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Edmund G. Memi Edmund G. Memi Edmund G. Memi Director, Communications Director, Communications Director, Communications The Boeing Company The Boeing Company The Boeing Company 281-226-4029 281-226-4029 281-226-4029 [email protected] [email protected] [email protected]

Susan Wells Susan Wells Susan Wells Space Exploration (Florida) Space Exploration (Florida) Space Exploration (Florida) The Boeing Company The Boeing Company The Boeing Company 321-264-8580 321-264-8580 321-264-8580 [email protected] [email protected] [email protected]

Adam Morgan Adam Morgan Adam Morgan Space Exploration (Houston) Space Exploration (Houston) Space Exploration (Houston) The Boeing Company The Boeing Company The Boeing Company 281-226-4030 281-226-4030 281-226-4030 [email protected] [email protected] [email protected]

Amy Reagan Amy Reagan Amy Reagan Space Exploration (Huntsville, Ala.) Space Exploration (Huntsville, Ala.) Space Exploration (Huntsville, Ala.) The Boeing Company The Boeing Company The Boeing Company 256-461-5888 256-461-5888 256-461-5888 [email protected] [email protected] [email protected]

Kennedy Space Center Launch Activities Kennedy Space Center Launch Activities Kennedy Space Center Launch Activities (recorded message) (recorded message) (recorded message) 321-867-2525 321-867-2525 321-867-2525

Kennedy Space Center Newsroom Kennedy Space Center Newsroom Kennedy Space Center Newsroom 321-867-2468 321-867-2468 321-867-2468

Johnson Space Center Newsroom Johnson Space Center Newsroom Johnson Space Center Newsroom 281-483-5111 281-483-5111 281-483-5111

Marshall Space Flight Center Newsroom Marshall Space Flight Center Newsroom Marshall Space Flight Center Newsroom 256-544-0034 256-544-0034 256-544-0034 A COLOR GUIDE TO THE STS-130 REPORTER'S A COLOR GUIDE TO THE STS-130 REPORTER'S A COLOR GUIDE TO THE STS-130 REPORTER'S SPACE FLIGHT NOTEPAD SPACE FLIGHT NOTEPAD SPACE FLIGHT NOTEPAD

NASA'S CONSTELLATION NASA'S CONSTELLATION NASA'S CONSTELLATION Gy-1 Gy-1 Gy-1 PROGRAM PROGRAM PROGRAM

BUILDING THE FUTURE BUILDING THE FUTURE BUILDING THE FUTURE S-1 S-1 S-1 OF FLIGHT TOGETHER OF FLIGHT TOGETHER OF FLIGHT TOGETHER

BOEING AND THE BOEING AND THE BOEING AND THE Gd-1 Gd-1 Gd-1 SPACE SHUTTLE SPACE SHUTTLE SPACE SHUTTLE

BOEING AND THE BOEING AND THE BOEING AND THE B-1 B-1 B-1 INTERNATIONAL SPACE STATION INTERNATIONAL SPACE STATION INTERNATIONAL SPACE STATION

SPACE SHUTTLE SPACE SHUTTLE SPACE SHUTTLE Y-1 Y-1 Y-1 MISSION FACTS MISSION FACTS MISSION FACTS

UPCOMING SPACE SHUTTLE UPCOMING SPACE SHUTTLE UPCOMING SPACE SHUTTLE G-1 G-1 G-1 MISSIONS MISSIONS MISSIONS NASA'S CONSTELLATION PROGRAM NASA'S CONSTELLATION PROGRAM NASA'S CONSTELLATION PROGRAM

The vision to inspire begins with a dream of hope and The vision to inspire begins with a dream of hope and The vision to inspire begins with a dream of hope and knowledge and ends with a mission of purpose and knowledge and ends with a mission of purpose and knowledge and ends with a mission of purpose and realization. In that manner, the nation’s space exploration realization. In that manner, the nation’s space exploration realization. In that manner, the nation’s space exploration embodies humankind’s instinctual desire to understand embodies humankind’s instinctual desire to understand embodies humankind’s instinctual desire to understand the fundamental questions about its existence and place the fundamental questions about its existence and place the fundamental questions about its existence and place in the cosmic universe. in the cosmic universe. in the cosmic universe.

Returning humans to the moon and then eventually send- Returning humans to the moon and then eventually send- Returning humans to the moon and then eventually send- ing them to Mars nurtures humankind’s desire to push ing them to Mars nurtures humankind’s desire to push ing them to Mars nurtures humankind’s desire to push beyond the boundaries of the obvious and open the doors beyond the boundaries of the obvious and open the doors beyond the boundaries of the obvious and open the doors to a new frontier of possibilities. to a new frontier of possibilities. to a new frontier of possibilities.

Just as legendary American explorers Meriwether Lewis Just as legendary American explorers Meriwether Lewis Just as legendary American explorers Meriwether Lewis and William Clark, Robert Peary, Charles Beebe and Neil and William Clark, Robert Peary, Charles Beebe and Neil and William Clark, Robert Peary, Charles Beebe and Neil Armstrong guided the world toward new experiences Armstrong guided the world toward new experiences Armstrong guided the world toward new experiences and possibilities on land, sea and space, the imminent and possibilities on land, sea and space, the imminent and possibilities on land, sea and space, the imminent pioneers of the universe will motivate future generations pioneers of the universe will motivate future generations pioneers of the universe will motivate future generations to investigate, cultivate and achieve. to investigate, cultivate and achieve. to investigate, cultivate and achieve.

During the past 20 years alone, astronomers have dis- During the past 20 years alone, astronomers have dis- During the past 20 years alone, astronomers have dis- covered the first solar system besides our own, lakes covered the first solar system besides our own, lakes covered the first solar system besides our own, lakes on Saturn’s moon Titan, the strongest evidence to date on Saturn’s moon Titan, the strongest evidence to date on Saturn’s moon Titan, the strongest evidence to date that water still flows occasionally on Mars, more than 100 that water still flows occasionally on Mars, more than 100 that water still flows occasionally on Mars, more than 100 planets orbiting other stars, and another planet in our solar planets orbiting other stars, and another planet in our solar planets orbiting other stars, and another planet in our solar system. The nation’s invigorated Space Exploration Policy system. The nation’s invigorated Space Exploration Policy system. The nation’s invigorated Space Exploration Policy will bolster these accomplishments by increasing the use will bolster these accomplishments by increasing the use will bolster these accomplishments by increasing the use of robotic exploration to maximize our understanding of of robotic exploration to maximize our understanding of of robotic exploration to maximize our understanding of the solar system and pave the way for more far-reaching the solar system and pave the way for more far-reaching the solar system and pave the way for more far-reaching crewed missions. crewed missions. crewed missions.

Robotic explorers will visit new worlds first to obtain Robotic explorers will visit new worlds first to obtain Robotic explorers will visit new worlds first to obtain scientific data, assess risks to astronauts, demonstrate scientific data, assess risks to astronauts, demonstrate scientific data, assess risks to astronauts, demonstrate breakthrough technologies, identify space resources and breakthrough technologies, identify space resources and breakthrough technologies, identify space resources and later send imagery back to Earth. Among these modern later send imagery back to Earth. Among these modern later send imagery back to Earth. Among these modern marvels are the highly successful and operational NASA marvels are the highly successful and operational NASA marvels are the highly successful and operational NASA Mars Exploration Rovers, Spirit and Opportunity, and the Mars Exploration Rovers, Spirit and Opportunity, and the Mars Exploration Rovers, Spirit and Opportunity, and the Phoenix Mars Lander. NASA’s Lunar Reconnaissance Phoenix Mars Lander. NASA’s Lunar Reconnaissance Phoenix Mars Lander. NASA’s Lunar Reconnaissance Orbiter, launched on June 18, 2009, is surveying lunar Orbiter, launched on June 18, 2009, is surveying lunar Orbiter, launched on June 18, 2009, is surveying lunar resources and identifying possible landing sites. resources and identifying possible landing sites. resources and identifying possible landing sites.

The space shuttle is still the workhorse of the space The space shuttle is still the workhorse of the space The space shuttle is still the workhorse of the space program and laying the foundation for crewed missions program and laying the foundation for crewed missions program and laying the foundation for crewed missions to the moon and to distant locations that now only robots to the moon and to distant locations that now only robots to the moon and to distant locations that now only robots travel. The lessons learned from this innovative machine travel. The lessons learned from this innovative machine travel. The lessons learned from this innovative machine and the space program’s Apollo heritage have spurred and the space program’s Apollo heritage have spurred and the space program’s Apollo heritage have spurred advancements in space transportation concepts that will advancements in space transportation concepts that will advancements in space transportation concepts that will become the ferry fleet of the future. become the ferry fleet of the future. become the ferry fleet of the future.

The space shuttle will retire in 2010, and its chief purpose The space shuttle will retire in 2010, and its chief purpose The space shuttle will retire in 2010, and its chief purpose until then will be to help finish assemble the International until then will be to help finish assemble the International until then will be to help finish assemble the International Space Station (ISS), fulfilling the commitment to our part- Space Station (ISS), fulfilling the commitment to our part- Space Station (ISS), fulfilling the commitment to our part- ner countries. Research on board the ISS will help us ner countries. Research on board the ISS will help us ner countries. Research on board the ISS will help us better understand and overcome the effects of human better understand and overcome the effects of human better understand and overcome the effects of human space flight on astronaut health, increasing the safety of space flight on astronaut health, increasing the safety of space flight on astronaut health, increasing the safety of planned future space missions. planned future space missions. planned future space missions.

Gy-1 Gy-1 Gy-1 The space station’s future vital role is evident with the The space station’s future vital role is evident with the The space station’s future vital role is evident with the United States’ plans for the new manned space explora- United States’ plans for the new manned space explora- United States’ plans for the new manned space explora- tion vehicle, being developed under NASA’s Constellation tion vehicle, being developed under NASA’s Constellation tion vehicle, being developed under NASA’s Constellation Program. The Orion crew exploration vehicle will succeed Program. The Orion crew exploration vehicle will succeed Program. The Orion crew exploration vehicle will succeed the space shuttle orbiter for ferrying crew and cargo to the space shuttle orbiter for ferrying crew and cargo to the space shuttle orbiter for ferrying crew and cargo to the ISS, along with the ability to make rendezvous with the ISS, along with the ability to make rendezvous with the ISS, along with the ability to make rendezvous with transportation elements in high Earth orbit. transportation elements in high Earth orbit. transportation elements in high Earth orbit.

Orion builds on the success of the Apollo command and Orion builds on the success of the Apollo command and Orion builds on the success of the Apollo command and lunar modules and benefits from recent advances in pro- lunar modules and benefits from recent advances in pro- lunar modules and benefits from recent advances in pro- pulsion and electronic technologies. Orion will be about pulsion and electronic technologies. Orion will be about pulsion and electronic technologies. Orion will be about three times larger than Apollo and ferry humans to the three times larger than Apollo and ferry humans to the three times larger than Apollo and ferry humans to the moon, Mars and other destinations in our solar system. moon, Mars and other destinations in our solar system. moon, Mars and other destinations in our solar system.

Orion is a modular system and comprises a service mod- Orion is a modular system and comprises a service mod- Orion is a modular system and comprises a service mod- ule, crew module, launch abort system and spacecraft ule, crew module, launch abort system and spacecraft ule, crew module, launch abort system and spacecraft adapter that mounts it to its launch vehicle. The crew adapter that mounts it to its launch vehicle. The crew adapter that mounts it to its launch vehicle. The crew module carries astronauts to the space station or to the module carries astronauts to the space station or to the module carries astronauts to the space station or to the moon. The service module carries the major support moon. The service module carries the major support moon. The service module carries the major support subsystems such as propulsion, avionics and thermal subsystems such as propulsion, avionics and thermal subsystems such as propulsion, avionics and thermal management. management. management.

The launch abort system will allow astronauts to escape The launch abort system will allow astronauts to escape The launch abort system will allow astronauts to escape the launch vehicle and land safely in the event of a launch- the launch vehicle and land safely in the event of a launch- the launch vehicle and land safely in the event of a launch- related problem. This launch abort system makes space- related problem. This launch abort system makes space- related problem. This launch abort system makes space- flight systems significantly safer during the most critical flight systems significantly safer during the most critical flight systems significantly safer during the most critical part of a mission, the launch. part of a mission, the launch. part of a mission, the launch.

The entire Orion configuration will launch from Kennedy The entire Orion configuration will launch from Kennedy The entire Orion configuration will launch from Kennedy Space Center aboard a new launch system called the Space Center aboard a new launch system called the Space Center aboard a new launch system called the Ares I crew launch vehicle. The rocket uses a single five- Ares I crew launch vehicle. The rocket uses a single five- Ares I crew launch vehicle. The rocket uses a single five- segment solid rocket booster, a derivative of the space segment solid rocket booster, a derivative of the space segment solid rocket booster, a derivative of the space shuttle’s solid rocket booster, for the first stage and a liquid shuttle’s solid rocket booster, for the first stage and a liquid shuttle’s solid rocket booster, for the first stage and a liquid oxygen/liquid hydrogen J-2X engine derived from the J-2 oxygen/liquid hydrogen J-2X engine derived from the J-2 oxygen/liquid hydrogen J-2X engine derived from the J-2 engine used on Apollo’s second stage for powering the engine used on Apollo’s second stage for powering the engine used on Apollo’s second stage for powering the Ares I second stage. Ares I can lift more than 55,000 lb Ares I second stage. Ares I can lift more than 55,000 lb Ares I second stage. Ares I can lift more than 55,000 lb to low Earth orbit. to low Earth orbit. to low Earth orbit.

During lunar missions, Orion will be mated in low Earth During lunar missions, Orion will be mated in low Earth During lunar missions, Orion will be mated in low Earth orbit with two additional modules: a propulsion module orbit with two additional modules: a propulsion module orbit with two additional modules: a propulsion module called the Earth departure stage that will allow Orion to called the Earth departure stage that will allow Orion to called the Earth departure stage that will allow Orion to travel to lunar orbit and a lunar lander, named Altair. Once travel to lunar orbit and a lunar lander, named Altair. Once travel to lunar orbit and a lunar lander, named Altair. Once in lunar orbit, the Altair lunar lander will separate from Orion in lunar orbit, the Altair lunar lander will separate from Orion in lunar orbit, the Altair lunar lander will separate from Orion and carry astronauts to the lunar surface. Orion, mean- and carry astronauts to the lunar surface. Orion, mean- and carry astronauts to the lunar surface. Orion, mean- while, will orbit autonomously for as many as 6 months while, will orbit autonomously for as many as 6 months while, will orbit autonomously for as many as 6 months while its crew explores the lunar surface. while its crew explores the lunar surface. while its crew explores the lunar surface.

The realization of extended human stays on the moon, The realization of extended human stays on the moon, The realization of extended human stays on the moon, like the opportunity Orion provides, is already helping fuel like the opportunity Orion provides, is already helping fuel like the opportunity Orion provides, is already helping fuel dialogue among private industry about space commerce dialogue among private industry about space commerce dialogue among private industry about space commerce opportunities. opportunities. opportunities.

Gy-2 Gy-2 Gy-2 Space commerce reflects industry’s desire to compete. Space commerce reflects industry’s desire to compete. Space commerce reflects industry’s desire to compete. Free market competition generates products and services Free market competition generates products and services Free market competition generates products and services that bolster consumer interest and global economies. that bolster consumer interest and global economies. that bolster consumer interest and global economies. So a partnership between NASA and private industry for So a partnership between NASA and private industry for So a partnership between NASA and private industry for commercial space profit-sharing will bring appreciable commercial space profit-sharing will bring appreciable commercial space profit-sharing will bring appreciable benefits on Earth. As an example, NASA’s Commercial benefits on Earth. As an example, NASA’s Commercial benefits on Earth. As an example, NASA’s Commercial Orbital Transportation Services (COTS) projects and its Orbital Transportation Services (COTS) projects and its Orbital Transportation Services (COTS) projects and its follow-on ISS Commercial Resupply Services (CRS) con- follow-on ISS Commercial Resupply Services (CRS) con- follow-on ISS Commercial Resupply Services (CRS) con- tracts are paving the way for a reliable commercial space tracts are paving the way for a reliable commercial space tracts are paving the way for a reliable commercial space transportation service for government and private sector transportation service for government and private sector transportation service for government and private sector companies to low Earth orbit when the space shuttle re- companies to low Earth orbit when the space shuttle re- companies to low Earth orbit when the space shuttle re- tires. The project will free the agency to focus on returning tires. The project will free the agency to focus on returning tires. The project will free the agency to focus on returning humans to the moon. humans to the moon. humans to the moon.

Another example of possible partnership between gov- Another example of possible partnership between gov- Another example of possible partnership between gov- ernment and private industry for mutual benefit involves ernment and private industry for mutual benefit involves ernment and private industry for mutual benefit involves mining on the moon. In September 2009, India's Chan- mining on the moon. In September 2009, India's Chan- mining on the moon. In September 2009, India's Chan- drayean-1, with its NASA-built Moon Mineralogy Mapper drayean-1, with its NASA-built Moon Mineralogy Mapper drayean-1, with its NASA-built Moon Mineralogy Mapper (M3), detected wavelengths of light reflected off the (M3), detected wavelengths of light reflected off the (M3), detected wavelengths of light reflected off the lunar surface that indicated the chemical bond between lunar surface that indicated the chemical bond between lunar surface that indicated the chemical bond between hydrogen and oxygen—the telltale sign of either water or hydrogen and oxygen—the telltale sign of either water or hydrogen and oxygen—the telltale sign of either water or hydroxyl. A company could be involved in extracting the hydroxyl. A company could be involved in extracting the hydroxyl. A company could be involved in extracting the elements of the compound as a means to manufacture elements of the compound as a means to manufacture elements of the compound as a means to manufacture rocket fuel on the moon. The fuel could power vehicles rocket fuel on the moon. The fuel could power vehicles rocket fuel on the moon. The fuel could power vehicles headed beyond the moon toward Mars, lowering space headed beyond the moon toward Mars, lowering space headed beyond the moon toward Mars, lowering space exploration costs. exploration costs. exploration costs.

NASA is also encouraging companies to develop com- NASA is also encouraging companies to develop com- NASA is also encouraging companies to develop com- mercial crew transportation systems to ferry astronauts mercial crew transportation systems to ferry astronauts mercial crew transportation systems to ferry astronauts back and forth from the International Space Station under back and forth from the International Space Station under back and forth from the International Space Station under its Commercial Crew Development (CCDev) program. its Commercial Crew Development (CCDev) program. its Commercial Crew Development (CCDev) program. Using a funded Space Act Agreement, NASA will use Using a funded Space Act Agreement, NASA will use Using a funded Space Act Agreement, NASA will use funds from the American Recovery and Reinvestment funds from the American Recovery and Reinvestment funds from the American Recovery and Reinvestment Act of 2009. By maturing the design and development of Act of 2009. By maturing the design and development of Act of 2009. By maturing the design and development of commercial crew spaceflight concepts and associated en- commercial crew spaceflight concepts and associated en- commercial crew spaceflight concepts and associated en- abling technologies and capabilities, the CCDev program abling technologies and capabilities, the CCDev program abling technologies and capabilities, the CCDev program allows companies to move toward full demonstration of allows companies to move toward full demonstration of allows companies to move toward full demonstration of commercial human spaceflight to low Earth orbit. In doing commercial human spaceflight to low Earth orbit. In doing commercial human spaceflight to low Earth orbit. In doing so, NASA may be able to reduce the gap in U.S. human so, NASA may be able to reduce the gap in U.S. human so, NASA may be able to reduce the gap in U.S. human spaceflight capability between the space shuttle's retire- spaceflight capability between the space shuttle's retire- spaceflight capability between the space shuttle's retire- ment and Orion's launch. ment and Orion's launch. ment and Orion's launch.

In the vastness of space, like all great frontiers, there is In the vastness of space, like all great frontiers, there is In the vastness of space, like all great frontiers, there is the potential to extend humankind’s knowledge far beyond the potential to extend humankind’s knowledge far beyond the potential to extend humankind’s knowledge far beyond what our imaginations can theorize. Thus, exploration what our imaginations can theorize. Thus, exploration what our imaginations can theorize. Thus, exploration and discovery are key agents of growth in society and and discovery are key agents of growth in society and and discovery are key agents of growth in society and can only lead to the nation’s technological, economic, can only lead to the nation’s technological, economic, can only lead to the nation’s technological, economic, social, international and intellectual advancement. The social, international and intellectual advancement. The social, international and intellectual advancement. The accomplishments of U.S. space explorers are a potent accomplishments of U.S. space explorers are a potent accomplishments of U.S. space explorers are a potent symbol of what the human spirit can achieve. symbol of what the human spirit can achieve. symbol of what the human spirit can achieve.

Gy-3 Gy-3 Gy-3 The Ares I Crew Launch Vehicle The Ares I Crew Launch Vehicle The Ares I Crew Launch Vehicle NASA is designing, testing, and evaluating hardware and NASA is designing, testing, and evaluating hardware and NASA is designing, testing, and evaluating hardware and related systems for the agency’s Ares I rocket—the vehicle related systems for the agency’s Ares I rocket—the vehicle related systems for the agency’s Ares I rocket—the vehicle that will carry a new generation of space explorers safely that will carry a new generation of space explorers safely that will carry a new generation of space explorers safely and reliably into orbit. and reliably into orbit. and reliably into orbit.

Under the goals of NASA’s exploration missions, Ares I is a Under the goals of NASA’s exploration missions, Ares I is a Under the goals of NASA’s exploration missions, Ares I is a chief component of the cost-effective space transportation chief component of the cost-effective space transportation chief component of the cost-effective space transportation infrastructure being developed by NASA’s Constellation infrastructure being developed by NASA’s Constellation infrastructure being developed by NASA’s Constellation Program. These transportation systems will carry human Program. These transportation systems will carry human Program. These transportation systems will carry human explorers back to the moon and other destinations in the explorers back to the moon and other destinations in the explorers back to the moon and other destinations in the solar system. solar system. solar system.

The Ares I effort includes multiple project element teams The Ares I effort includes multiple project element teams The Ares I effort includes multiple project element teams working at NASA centers and contract organizations around working at NASA centers and contract organizations around working at NASA centers and contract organizations around the nation and is led by the Ares Projects at NASA’s Marshall the nation and is led by the Ares Projects at NASA’s Marshall the nation and is led by the Ares Projects at NASA’s Marshall Space Flight Center in Huntsville, Ala. Together, these Space Flight Center in Huntsville, Ala. Together, these Space Flight Center in Huntsville, Ala. Together, these teams are designing and developing vehicle hardware, teams are designing and developing vehicle hardware, teams are designing and developing vehicle hardware, evolving proven technologies, and testing components evolving proven technologies, and testing components evolving proven technologies, and testing components and systems. and systems. and systems.

Ares I is an in-line, two-stage rocket topped by the Orion Ares I is an in-line, two-stage rocket topped by the Orion Ares I is an in-line, two-stage rocket topped by the Orion capsule, its service module, and a launch abort system. The capsule, its service module, and a launch abort system. The capsule, its service module, and a launch abort system. The combination of the rocket’s configuration and Orion’s launch combination of the rocket’s configuration and Orion’s launch combination of the rocket’s configuration and Orion’s launch abort system, which can move astronauts away quickly in abort system, which can move astronauts away quickly in abort system, which can move astronauts away quickly in case of a launch emergency, will improve crew safety. case of a launch emergency, will improve crew safety. case of a launch emergency, will improve crew safety.

The launch vehicle’s first stage is a single, five-segment The launch vehicle’s first stage is a single, five-segment The launch vehicle’s first stage is a single, five-segment reusable solid rocket booster, derived from the Space Shuttle reusable solid rocket booster, derived from the Space Shuttle reusable solid rocket booster, derived from the Space Shuttle Program’s four-segment reusable solid rocket booster, which Program’s four-segment reusable solid rocket booster, which Program’s four-segment reusable solid rocket booster, which burns a specially formulated and shaped solid propellant burns a specially formulated and shaped solid propellant burns a specially formulated and shaped solid propellant called polybutadiene acrylonitrile (PBAN). A newly designed called polybutadiene acrylonitrile (PBAN). A newly designed called polybutadiene acrylonitrile (PBAN). A newly designed forward adapter called a frustum will mate the vehicle’s forward adapter called a frustum will mate the vehicle’s forward adapter called a frustum will mate the vehicle’s first stage to the second and will be equipped with booster first stage to the second and will be equipped with booster first stage to the second and will be equipped with booster separation motors to disconnect the stages during ascent. separation motors to disconnect the stages during ascent. separation motors to disconnect the stages during ascent.

The second, or upper, stage is being designed at Marshall. The second, or upper, stage is being designed at Marshall. The second, or upper, stage is being designed at Marshall. Much like the upper stage for the Ares V cargo launch vehicle, Much like the upper stage for the Ares V cargo launch vehicle, Much like the upper stage for the Ares V cargo launch vehicle, the Ares I upper stage is propelled by a J-2X main engine the Ares I upper stage is propelled by a J-2X main engine the Ares I upper stage is propelled by a J-2X main engine fueled with liquid oxygen and liquid hydrogen. fueled with liquid oxygen and liquid hydrogen. fueled with liquid oxygen and liquid hydrogen.

The J-2X is an evolved variation of two historic predecessors: The J-2X is an evolved variation of two historic predecessors: The J-2X is an evolved variation of two historic predecessors: the powerful J-2 upper-stage engine that propelled the the powerful J-2 upper-stage engine that propelled the the powerful J-2 upper-stage engine that propelled the Apollo-era Saturn IB and Saturn V rockets to the moon and Apollo-era Saturn IB and Saturn V rockets to the moon and Apollo-era Saturn IB and Saturn V rockets to the moon and the J-2S, a simplified version of the J-2 developed and tested the J-2S, a simplified version of the J-2 developed and tested the J-2S, a simplified version of the J-2 developed and tested in the early 1970s. in the early 1970s. in the early 1970s.

Ares I has two missions: lofting astronauts (or cargo) to the Ares I has two missions: lofting astronauts (or cargo) to the Ares I has two missions: lofting astronauts (or cargo) to the ISS—approximately 52,000 lb—or astronauts to low Earth ISS—approximately 52,000 lb—or astronauts to low Earth ISS—approximately 52,000 lb—or astronauts to low Earth orbit for rendezvous with the Ares V Earth departure stage orbit for rendezvous with the Ares V Earth departure stage orbit for rendezvous with the Ares V Earth departure stage for missions to the moon (56,000 lb). for missions to the moon (56,000 lb). for missions to the moon (56,000 lb).

During the first 2 1/2 minutes of flight, the first-stage booster During the first 2 1/2 minutes of flight, the first-stage booster During the first 2 1/2 minutes of flight, the first-stage booster powers the vehicle to an altitude of about 187,400 feet (35.5 powers the vehicle to an altitude of about 187,400 feet (35.5 powers the vehicle to an altitude of about 187,400 feet (35.5 miles) and a speed of Mach 5.7. After its propellant is spent, miles) and a speed of Mach 5.7. After its propellant is spent, miles) and a speed of Mach 5.7. After its propellant is spent, the reusable booster separates, and the upper stage’s the reusable booster separates, and the upper stage’s the reusable booster separates, and the upper stage’s J-2X engine ignites and powers the Orion spacecraft to an J-2X engine ignites and powers the Orion spacecraft to an J-2X engine ignites and powers the Orion spacecraft to an altitude of about 425,328 feet (81 miles). Then, the upper altitude of about 425,328 feet (81 miles). Then, the upper altitude of about 425,328 feet (81 miles). Then, the upper

Gy-4 Gy-4 Gy-4 stage separates, and Orion’s service module propulsion stage separates, and Orion’s service module propulsion stage separates, and Orion’s service module propulsion system completes the trip to a circular orbit of 976,800 feet system completes the trip to a circular orbit of 976,800 feet system completes the trip to a circular orbit of 976,800 feet (185 miles) above Earth. (185 miles) above Earth. (185 miles) above Earth.

Once in orbit, Orion and its service module will rendezvous Once in orbit, Orion and its service module will rendezvous Once in orbit, Orion and its service module will rendezvous and dock either with the ISS or with the Altair lunar lander and dock either with the ISS or with the Altair lunar lander and dock either with the ISS or with the Altair lunar lander and Earth departure stage that will send the astronauts on and Earth departure stage that will send the astronauts on and Earth departure stage that will send the astronauts on their way to the moon. their way to the moon. their way to the moon.

The first Ares I test flight, called Ares I-X, successfully The first Ares I test flight, called Ares I-X, successfully The first Ares I test flight, called Ares I-X, successfully launched on Oct. 28, 2009. The first crewed flight of Orion launched on Oct. 28, 2009. The first crewed flight of Orion launched on Oct. 28, 2009. The first crewed flight of Orion is planned for no later than 2015, with crew transportation to is planned for no later than 2015, with crew transportation to is planned for no later than 2015, with crew transportation to the ISS following within the same decade and the first lunar the ISS following within the same decade and the first lunar the ISS following within the same decade and the first lunar mission scheduled for the 2020 timeframe. mission scheduled for the 2020 timeframe. mission scheduled for the 2020 timeframe.

Participating agency facilities include NASA’s Johnson Participating agency facilities include NASA’s Johnson Participating agency facilities include NASA’s Johnson Space Center, which is responsible for the Orion spacecraft Space Center, which is responsible for the Orion spacecraft Space Center, which is responsible for the Orion spacecraft and flight operations projects; Stennis Space Center near and flight operations projects; Stennis Space Center near and flight operations projects; Stennis Space Center near Bay St. Louis, Miss., which is primarily responsible for J-2X Bay St. Louis, Miss., which is primarily responsible for J-2X Bay St. Louis, Miss., which is primarily responsible for J-2X testing; NASA Glenn Research Center, which is responsible testing; NASA Glenn Research Center, which is responsible testing; NASA Glenn Research Center, which is responsible for developing the Ares I-X upper stage mass simulator and for developing the Ares I-X upper stage mass simulator and for developing the Ares I-X upper stage mass simulator and Ares I upper stage power, thrust vector control, and sensor Ares I upper stage power, thrust vector control, and sensor Ares I upper stage power, thrust vector control, and sensor development; NASA’s Langley Research Center in Hampton, development; NASA’s Langley Research Center in Hampton, development; NASA’s Langley Research Center in Hampton, Va., which is responsible for Ares I-X flight test vehicle Va., which is responsible for Ares I-X flight test vehicle Va., which is responsible for Ares I-X flight test vehicle integration and Orion launch abort system development, and integration and Orion launch abort system development, and integration and Orion launch abort system development, and for support to flight mechanics and structure development; for support to flight mechanics and structure development; for support to flight mechanics and structure development; NASA’s Ames Research Center in Sunnyvale, Calif., which is NASA’s Ames Research Center in Sunnyvale, Calif., which is NASA’s Ames Research Center in Sunnyvale, Calif., which is responsible for Ares analysis support, mission and ground responsible for Ares analysis support, mission and ground responsible for Ares analysis support, mission and ground operations support, and program systems engineering operations support, and program systems engineering operations support, and program systems engineering and integration; NASA’s Michoud Assembly Facility in New and integration; NASA’s Michoud Assembly Facility in New and integration; NASA’s Michoud Assembly Facility in New Orleans, which will manufacture and assemble the Ares I Orleans, which will manufacture and assemble the Ares I Orleans, which will manufacture and assemble the Ares I upper stage, the core stage, and the Earth departure stage upper stage, the core stage, and the Earth departure stage upper stage, the core stage, and the Earth departure stage of the Ares V cargo launch vehicle, and the Orion crew of the Ares V cargo launch vehicle, and the Orion crew of the Ares V cargo launch vehicle, and the Orion crew exploration vehicle; and NASA’s Kennedy Space Center, exploration vehicle; and NASA’s Kennedy Space Center, exploration vehicle; and NASA’s Kennedy Space Center, Fla., which is home to all Constellation launch operations Fla., which is home to all Constellation launch operations Fla., which is home to all Constellation launch operations and associated ground activities. and associated ground activities. and associated ground activities.

ATK Launch Systems near Brigham City, Utah, is the prime ATK Launch Systems near Brigham City, Utah, is the prime ATK Launch Systems near Brigham City, Utah, is the prime contractor for the first stage. Pratt & Whitney Rocketdyne contractor for the first stage. Pratt & Whitney Rocketdyne contractor for the first stage. Pratt & Whitney Rocketdyne in Canoga Park, Calif., is the prime contractor for the Ares I in Canoga Park, Calif., is the prime contractor for the Ares I in Canoga Park, Calif., is the prime contractor for the Ares I upper stage J-2X engine. The Boeing Co. in Huntsville, Ala., upper stage J-2X engine. The Boeing Co. in Huntsville, Ala., upper stage J-2X engine. The Boeing Co. in Huntsville, Ala., is the prime contractor responsible for design and production is the prime contractor responsible for design and production is the prime contractor responsible for design and production of the upper stage and instrument unit avionics. of the upper stage and instrument unit avionics. of the upper stage and instrument unit avionics.

For additional information about the Ares Project, as well as For additional information about the Ares Project, as well as For additional information about the Ares Project, as well as images, news releases, and more, please visit http://www. images, news releases, and more, please visit http://www. images, news releases, and more, please visit http://www. nasa.gov/ares. You can also follow the latest developments nasa.gov/ares. You can also follow the latest developments nasa.gov/ares. You can also follow the latest developments with the Ares rockets by checking the following sites: with the Ares rockets by checking the following sites: with the Ares rockets by checking the following sites:

Ares on Facebook: http://www.facebook.com/ Ares on Facebook: http://www.facebook.com/ Ares on Facebook: http://www.facebook.com/ NASA.Ares NASA.Ares NASA.Ares

Ares TV on YouTube: http://www.youtube.com/AresTV Ares TV on YouTube: http://www.youtube.com/AresTV Ares TV on YouTube: http://www.youtube.com/AresTV

Ares on TeacherTube: http://www.teachertube.com/ Ares on TeacherTube: http://www.teachertube.com/ Ares on TeacherTube: http://www.teachertube.com/ videoList.php?pg=videonew&cid=38 videoList.php?pg=videonew&cid=38 videoList.php?pg=videonew&cid=38

NASA Ares on Twitter: http://twitter.com/NASA_Ares NASA Ares on Twitter: http://twitter.com/NASA_Ares NASA Ares on Twitter: http://twitter.com/NASA_Ares

Gy-5 Gy-5 Gy-5 Launch Abort System Launch Abort System Launch Abort System

Orion Crew Exploration Vehicle Orion Crew Exploration Vehicle Orion Crew Exploration Vehicle

(Crew Module/Service Module) (Crew Module/Service Module) (Crew Module/Service Module)

Encapsulated Service Encapsulated Service Encapsulated Service Module Panels Module Panels Module Panels

Instrument Unit Instrument Unit Instrument Unit

Upper Stage Upper Stage Upper Stage

J-2X Upper-Stage Engine J-2X Upper-Stage Engine J-2X Upper-Stage Engine

Forward Frustum Forward Frustum Forward Frustum

Interstage Interstage Interstage

First Stage First Stage First Stage (5-Segment RSRB) (5-Segment RSRB) (5-Segment RSRB)

Ares I Ares I Ares I

Gy-6 Gy-6 Gy-6 The Orion Crew Exploration Vehicle The Orion Crew Exploration Vehicle The Orion Crew Exploration Vehicle

Building on the best of Apollo and shuttle technology, Building on the best of Apollo and shuttle technology, Building on the best of Apollo and shuttle technology, NASA is creating a 21st century exploration system that NASA is creating a 21st century exploration system that NASA is creating a 21st century exploration system that will be safe, affordable, reliable, versatile, and reusable. will be safe, affordable, reliable, versatile, and reusable. will be safe, affordable, reliable, versatile, and reusable. Orion’s size will allow it to transport crew members to the Orion’s size will allow it to transport crew members to the Orion’s size will allow it to transport crew members to the ISS and to lunar orbit. It will be able to rendezvous with ISS and to lunar orbit. It will be able to rendezvous with ISS and to lunar orbit. It will be able to rendezvous with the Altair lunar lander and an Earth departure stage in the Altair lunar lander and an Earth departure stage in the Altair lunar lander and an Earth departure stage in low Earth orbit to carry the crew members to the moon. low Earth orbit to carry the crew members to the moon. low Earth orbit to carry the crew members to the moon. In the future, Orion could rendezvous in low Earth orbit In the future, Orion could rendezvous in low Earth orbit In the future, Orion could rendezvous in low Earth orbit with vehicles that will take explorers to other destinations with vehicles that will take explorers to other destinations with vehicles that will take explorers to other destinations in our solar system such as Mars. in our solar system such as Mars. in our solar system such as Mars.

The Orion crew exploration vehicle will be launched into The Orion crew exploration vehicle will be launched into The Orion crew exploration vehicle will be launched into Earth’s orbit by the Ares I crew launch vehicle. To maximize Earth’s orbit by the Ares I crew launch vehicle. To maximize Earth’s orbit by the Ares I crew launch vehicle. To maximize crew safety, Orion has incorporated a launch abort system crew safety, Orion has incorporated a launch abort system crew safety, Orion has incorporated a launch abort system to carry the crew safely away from possible life-threatening to carry the crew safely away from possible life-threatening to carry the crew safely away from possible life-threatening scenarios. scenarios. scenarios.

For missions to the moon, Orion will dock with Altair and For missions to the moon, Orion will dock with Altair and For missions to the moon, Orion will dock with Altair and an Earth departure stage in low Earth orbit. The Earth an Earth departure stage in low Earth orbit. The Earth an Earth departure stage in low Earth orbit. The Earth departure stage will propel Orion and Altair to the moon. departure stage will propel Orion and Altair to the moon. departure stage will propel Orion and Altair to the moon. Once they have reached the moon’s orbit, astronauts will Once they have reached the moon’s orbit, astronauts will Once they have reached the moon’s orbit, astronauts will use Altair to travel to the moon’s surface. Orion will stay in use Altair to travel to the moon’s surface. Orion will stay in use Altair to travel to the moon’s surface. Orion will stay in lunar orbit up to 210 days, awaiting return of the crew. lunar orbit up to 210 days, awaiting return of the crew. lunar orbit up to 210 days, awaiting return of the crew.

After a stay on the lunar surface, the crew will return to the After a stay on the lunar surface, the crew will return to the After a stay on the lunar surface, the crew will return to the orbiting Orion, using Altair as its ascent vehicle. Once the orbiting Orion, using Altair as its ascent vehicle. Once the orbiting Orion, using Altair as its ascent vehicle. Once the crew has reunited with Orion and Altair has been released, crew has reunited with Orion and Altair has been released, crew has reunited with Orion and Altair has been released, the service module main engine will provide the power for the service module main engine will provide the power for the service module main engine will provide the power for Orion to break out of lunar orbit and return to Earth. Orion to break out of lunar orbit and return to Earth. Orion to break out of lunar orbit and return to Earth.

The service module supports the crew module until the The service module supports the crew module until the The service module supports the crew module until the two modules separate just before reentering Earth’s two modules separate just before reentering Earth’s two modules separate just before reentering Earth’s atmosphere. The Orion crew module will reenter Earth’s atmosphere. The Orion crew module will reenter Earth’s atmosphere. The Orion crew module will reenter Earth’s atmosphere and, with the use of parachutes, safely return atmosphere and, with the use of parachutes, safely return atmosphere and, with the use of parachutes, safely return the astronauts back to Earth. the astronauts back to Earth. the astronauts back to Earth.

Development of Orion and associated Constellation Pro- Development of Orion and associated Constellation Pro- Development of Orion and associated Constellation Pro- gram elements is a joint effort involving every NASA center gram elements is a joint effort involving every NASA center gram elements is a joint effort involving every NASA center and is led by the Orion Project Office at Johnson Space and is led by the Orion Project Office at Johnson Space and is led by the Orion Project Office at Johnson Space Center (JSC) in Houston. Lockheed Martin is NASA’s Center (JSC) in Houston. Lockheed Martin is NASA’s Center (JSC) in Houston. Lockheed Martin is NASA’s prime contractor for design, development, testing, and prime contractor for design, development, testing, and prime contractor for design, development, testing, and construction of Orion. construction of Orion. construction of Orion. Number of Crew 4 lunar 4 ISS Number of Crew 4 lunar 4 ISS Number of Crew 4 lunar 4 ISS Diameter 5 m 16.5 ft Diameter 5 m 16.5 ft Diameter 5 m 16.5 ft Pressurized Volume 20 m3 690.6 ft3 Pressurized Volume 20 m3 690.6 ft3 Pressurized Volume 20 m3 690.6 ft3 Habitable Volume 9 m3 316 ft3 Habitable Volume 9 m3 316 ft3 Habitable Volume 9 m3 316 ft3 Effective Mass to Orbit Effective Mass to Orbit Effective Mass to Orbit – Lunar 21,877 kg 48,231 lb – Lunar 21,877 kg 48,231 lb – Lunar 21,877 kg 48,231 lb – ISS 19,142 kg 42,201 lb – ISS 19,142 kg 42,201 lb – ISS 19,142 kg 42,201 lb Total Propulsive Capability Total Propulsive Capability Total Propulsive Capability (Service Module Engine) 1,595 m/s 5,233 ft/s (Service Module Engine) 1,595 m/s 5,233 ft/s (Service Module Engine) 1,595 m/s 5,233 ft/s Lunar Return Payload 100 kg 220 lb Lunar Return Payload 100 kg 220 lb Lunar Return Payload 100 kg 220 lb Landing Weight 8,591 kg 18,939 lb Landing Weight 8,591 kg 18,939 lb Landing Weight 8,591 kg 18,939 lb

Gy-7 Gy-7 Gy-7 Launch Abort System Launch Abort System Launch Abort System

Crew Module Crew Module Crew Module

Service Module Service Module Service Module

Spacecraft Adapter Spacecraft Adapter Spacecraft Adapter

Orion Crew Exploration Vehicle Orion Crew Exploration Vehicle Orion Crew Exploration Vehicle

Gy-8 Gy-8 Gy-8 BUILDING THE FUTURE OF FLIGHT TOGETHER BUILDING THE FUTURE OF FLIGHT TOGETHER BUILDING THE FUTURE OF FLIGHT TOGETHER

From their common beginnings as builders of biplanes to From their common beginnings as builders of biplanes to From their common beginnings as builders of biplanes to the exploration of space, Boeing, North American Avia- the exploration of space, Boeing, North American Avia- the exploration of space, Boeing, North American Avia- tion, and McDonnell Douglas share a unique aerospace tion, and McDonnell Douglas share a unique aerospace tion, and McDonnell Douglas share a unique aerospace heritage. Today, as one company, Boeing continues to heritage. Today, as one company, Boeing continues to heritage. Today, as one company, Boeing continues to pioneer the exploration of space. pioneer the exploration of space. pioneer the exploration of space. As the Space Age dawned, each company translated its As the Space Age dawned, each company translated its As the Space Age dawned, each company translated its aeronautical expertise into humankind’s greatest engineer- aeronautical expertise into humankind’s greatest engineer- aeronautical expertise into humankind’s greatest engineer- ing feat—sending astronauts to the moon and returning ing feat—sending astronauts to the moon and returning ing feat—sending astronauts to the moon and returning them safely to Earth. them safely to Earth. them safely to Earth. Following the success of the Apollo program, the compa- Following the success of the Apollo program, the compa- Following the success of the Apollo program, the compa- nies continued working together in space. nies continued working together in space. nies continued working together in space. When North American Rockwell began developing six When North American Rockwell began developing six When North American Rockwell began developing six space shuttles, Boeing and McDonnell Douglas joined space shuttles, Boeing and McDonnell Douglas joined space shuttles, Boeing and McDonnell Douglas joined as key partners. as key partners. as key partners. McDonnell Douglas developed aft propulsion pods to McDonnell Douglas developed aft propulsion pods to McDonnell Douglas developed aft propulsion pods to control the shuttle while in orbit. It also provided structural control the shuttle while in orbit. It also provided structural control the shuttle while in orbit. It also provided structural parts for the boosters that lift shuttles into space. parts for the boosters that lift shuttles into space. parts for the boosters that lift shuttles into space. Boeing modified two 747 jetliners to piggyback shuttles Boeing modified two 747 jetliners to piggyback shuttles Boeing modified two 747 jetliners to piggyback shuttles from landing sites in California to launch pads in Florida. from landing sites in California to launch pads in Florida. from landing sites in California to launch pads in Florida. One of the jumbo jets also helped test the first shuttle, One of the jumbo jets also helped test the first shuttle, One of the jumbo jets also helped test the first shuttle, which was released from the 747 at an altitude of 22,800 which was released from the 747 at an altitude of 22,800 which was released from the 747 at an altitude of 22,800 feet before gliding to a perfect landing. feet before gliding to a perfect landing. feet before gliding to a perfect landing. In addition, Boeing developed the Inertial Upper Stage In addition, Boeing developed the Inertial Upper Stage In addition, Boeing developed the Inertial Upper Stage used by shuttle crews to boost satellites into higher used by shuttle crews to boost satellites into higher used by shuttle crews to boost satellites into higher orbits. orbits. orbits. The shuttle fleet has been transporting humans and cargo The shuttle fleet has been transporting humans and cargo The shuttle fleet has been transporting humans and cargo to space since 1981 and has completed 127 missions. In- to space since 1981 and has completed 127 missions. In- to space since 1981 and has completed 127 missions. In- novations in the shuttle’s design, such as a “glass cockpit,” novations in the shuttle’s design, such as a “glass cockpit,” novations in the shuttle’s design, such as a “glass cockpit,” much like ones in modern airliners, improve safety and much like ones in modern airliners, improve safety and much like ones in modern airliners, improve safety and performance. performance. performance. Even before the mergers, McDonnell Douglas and Boeing Even before the mergers, McDonnell Douglas and Boeing Even before the mergers, McDonnell Douglas and Boeing were part of the Boeing-led program to develop the Inter- were part of the Boeing-led program to develop the Inter- were part of the Boeing-led program to develop the Inter- national Space Station. They produced key components, national Space Station. They produced key components, national Space Station. They produced key components, including the massive solar panels, the U.S. Laboratory including the massive solar panels, the U.S. Laboratory including the massive solar panels, the U.S. Laboratory “Destiny,” and the truss that forms the station’s structural “Destiny,” and the truss that forms the station’s structural “Destiny,” and the truss that forms the station’s structural backbone. backbone. backbone. Since then, Boeing was named NASA’s lead contractor Since then, Boeing was named NASA’s lead contractor Since then, Boeing was named NASA’s lead contractor for the ISS. This includes design to delivery of U.S.-built for the ISS. This includes design to delivery of U.S.-built for the ISS. This includes design to delivery of U.S.-built elements. Boeing is also the major subcontractor to United elements. Boeing is also the major subcontractor to United elements. Boeing is also the major subcontractor to United Space Alliance for NASA’s Space Flight Operations Con- Space Alliance for NASA’s Space Flight Operations Con- Space Alliance for NASA’s Space Flight Operations Con- tract. Boeing is responsible for sustaining engineering sup- tract. Boeing is responsible for sustaining engineering sup- tract. Boeing is responsible for sustaining engineering sup- port to operations throughout all missions. Additionally, the port to operations throughout all missions. Additionally, the port to operations throughout all missions. Additionally, the Boeing team provides overall shuttle system and payload Boeing team provides overall shuttle system and payload Boeing team provides overall shuttle system and payload integration services, and launch and mission support. integration services, and launch and mission support. integration services, and launch and mission support. Once completed, the million-pound space station will in- Once completed, the million-pound space station will in- Once completed, the million-pound space station will in- clude six laboratories and have an internal volume roughly clude six laboratories and have an internal volume roughly clude six laboratories and have an internal volume roughly equivalent to the passenger cabin of 1.5 747 jumbo jets. equivalent to the passenger cabin of 1.5 747 jumbo jets. equivalent to the passenger cabin of 1.5 747 jumbo jets. The orbital research facility entered its tenth year of con- The orbital research facility entered its tenth year of con- The orbital research facility entered its tenth year of con- tinuous human presence in November 2009. tinuous human presence in November 2009. tinuous human presence in November 2009.

S-1 S-1 S-1 BOEING AND THE SPACE SHUTTLE BOEING AND THE SPACE SHUTTLE BOEING AND THE SPACE SHUTTLE

In addition to manufacturing the space shuttle, The Boeing In addition to manufacturing the space shuttle, The Boeing In addition to manufacturing the space shuttle, The Boeing Company also plays a multitude of behind-the-scene roles Company also plays a multitude of behind-the-scene roles Company also plays a multitude of behind-the-scene roles integral to NASA’s human space flight program. integral to NASA’s human space flight program. integral to NASA’s human space flight program. Boeing’s Space Exploration, a unit of Boeing Defense, Boeing’s Space Exploration, a unit of Boeing Defense, Boeing’s Space Exploration, a unit of Boeing Defense, Space and Security (BDS), which is headquartered in St. Space and Security (BDS), which is headquartered in St. Space and Security (BDS), which is headquartered in St. Louis, performs the work. Space Exploration is headquar- Louis, performs the work. Space Exploration is headquar- Louis, performs the work. Space Exploration is headquar- tered in Houston and also operates facilities in Huntington tered in Houston and also operates facilities in Huntington tered in Houston and also operates facilities in Huntington Beach, Calif.; Huntsville, Ala.; Kennedy Space Center, Fla.; Beach, Calif.; Huntsville, Ala.; Kennedy Space Center, Fla.; Beach, Calif.; Huntsville, Ala.; Kennedy Space Center, Fla.; and Palmdale, Calif. and Palmdale, Calif. and Palmdale, Calif. Boeing is the major subcontractor to United Space Alliance Boeing is the major subcontractor to United Space Alliance Boeing is the major subcontractor to United Space Alliance (USA), NASA’s prime contractor for space shuttle opera- (USA), NASA’s prime contractor for space shuttle opera- (USA), NASA’s prime contractor for space shuttle opera- tions. Headquartered in Houston, Texas, United Space tions. Headquartered in Houston, Texas, United Space tions. Headquartered in Houston, Texas, United Space Alliance is one of the world's leading space operations Alliance is one of the world's leading space operations Alliance is one of the world's leading space operations companies. Established in 1995 as a Limited Liability companies. Established in 1995 as a Limited Liability companies. Established in 1995 as a Limited Liability Company (LLC), USA is equally owned by The Boeing Company (LLC), USA is equally owned by The Boeing Company (LLC), USA is equally owned by The Boeing Company (NYSE:BA) and Lockheed Martin Corporation Company (NYSE:BA) and Lockheed Martin Corporation Company (NYSE:BA) and Lockheed Martin Corporation (NYSE:LMT) and has employees working in Florida, Ala- (NYSE:LMT) and has employees working in Florida, Ala- (NYSE:LMT) and has employees working in Florida, Ala- bama, California, Washington, D.C., and Russia. bama, California, Washington, D.C., and Russia. bama, California, Washington, D.C., and Russia. Boeing has provided design engineering and support for Boeing has provided design engineering and support for Boeing has provided design engineering and support for the shuttle fleet since the first flight in 1981. Boeing engi- the shuttle fleet since the first flight in 1981. Boeing engi- the shuttle fleet since the first flight in 1981. Boeing engi- neers are actively involved in the design and development neers are actively involved in the design and development neers are actively involved in the design and development work required to fulfill America’s space exploration goals, work required to fulfill America’s space exploration goals, work required to fulfill America’s space exploration goals, using the existing shuttle experience and knowledge as a using the existing shuttle experience and knowledge as a using the existing shuttle experience and knowledge as a stepping-stone to the next space exploration vehicle. stepping-stone to the next space exploration vehicle. stepping-stone to the next space exploration vehicle. Boeing’s space shuttle work is organized into the follow- Boeing’s space shuttle work is organized into the follow- Boeing’s space shuttle work is organized into the follow- ing areas: ing areas: ing areas: Ongoing Engineering Support: Boeing serves as the technical Ongoing Engineering Support: Boeing serves as the technical Ongoing Engineering Support: Boeing serves as the technical expert to NASA and USA on the design and operations of the expert to NASA and USA on the design and operations of the expert to NASA and USA on the design and operations of the orbiter fleet to ensure its continued safety, flight readiness, orbiter fleet to ensure its continued safety, flight readiness, orbiter fleet to ensure its continued safety, flight readiness, efficiency, and overall mission success. Activities range efficiency, and overall mission success. Activities range efficiency, and overall mission success. Activities range from designing new system modifications and upgrades to from designing new system modifications and upgrades to from designing new system modifications and upgrades to resolving day-to-day issues and mission anomalies. resolving day-to-day issues and mission anomalies. resolving day-to-day issues and mission anomalies. System and Payload Integration: Boeing identifies overall System and Payload Integration: Boeing identifies overall System and Payload Integration: Boeing identifies overall shuttle system (orbiter, Space Shuttle Main Engines, shuttle system (orbiter, Space Shuttle Main Engines, shuttle system (orbiter, Space Shuttle Main Engines, external tank, and solid rocket boosters) and payload re- external tank, and solid rocket boosters) and payload re- external tank, and solid rocket boosters) and payload re- quirements during all shuttle operations phases: ground quirements during all shuttle operations phases: ground quirements during all shuttle operations phases: ground operations and checkout, ascent, on-orbit operations, operations and checkout, ascent, on-orbit operations, operations and checkout, ascent, on-orbit operations, reentry, landing, and ferry flight activities. It also ensures reentry, landing, and ferry flight activities. It also ensures reentry, landing, and ferry flight activities. It also ensures the complementary operation of shuttle system elements, the complementary operation of shuttle system elements, the complementary operation of shuttle system elements, payloads, and ground systems. Activities range from eval- payloads, and ground systems. Activities range from eval- payloads, and ground systems. Activities range from eval- uating external structural loads, aerodynamics, heating, uating external structural loads, aerodynamics, heating, uating external structural loads, aerodynamics, heating, and guidance to developing payload support hardware. and guidance to developing payload support hardware. and guidance to developing payload support hardware. Orbiter Maintenance and Modifications: A technical team Orbiter Maintenance and Modifications: A technical team Orbiter Maintenance and Modifications: A technical team at Kennedy Space Center supports periodic orbiter ma- at Kennedy Space Center supports periodic orbiter ma- at Kennedy Space Center supports periodic orbiter ma- jor modifications, during which each vehicle receives a jor modifications, during which each vehicle receives a jor modifications, during which each vehicle receives a comprehensive structural inspection and modifications comprehensive structural inspection and modifications comprehensive structural inspection and modifications designed to reduce program maintenance costs, expand designed to reduce program maintenance costs, expand designed to reduce program maintenance costs, expand shuttle mission capabilities, and improve operations, shuttle mission capabilities, and improve operations, shuttle mission capabilities, and improve operations, safety, and reliability. safety, and reliability. safety, and reliability.

Gd-1 Gd-1 Gd-1 Payload Ground Operations: Under the Checkout, Payload Ground Operations: Under the Checkout, Payload Ground Operations: Under the Checkout, Assembly, and Payload Processing Services (CAPPS) Assembly, and Payload Processing Services (CAPPS) Assembly, and Payload Processing Services (CAPPS) contract at NASA’s Kennedy Space Center, Boeing per- contract at NASA’s Kennedy Space Center, Boeing per- contract at NASA’s Kennedy Space Center, Boeing per- forms engineering and facilities support and maintenance forms engineering and facilities support and maintenance forms engineering and facilities support and maintenance activities related to preparing payloads for launch in the activities related to preparing payloads for launch in the activities related to preparing payloads for launch in the shuttle’s payload bay. Processing a human space flight shuttle’s payload bay. Processing a human space flight shuttle’s payload bay. Processing a human space flight payload involves complex scheduling and logistics and payload involves complex scheduling and logistics and payload involves complex scheduling and logistics and precise testing to ensure the payload can communicate precise testing to ensure the payload can communicate precise testing to ensure the payload can communicate with the orbiter and ground stations. The payloads can with the orbiter and ground stations. The payloads can with the orbiter and ground stations. The payloads can include scientific instruments, interplanetary spacecraft, include scientific instruments, interplanetary spacecraft, include scientific instruments, interplanetary spacecraft, research laboratory modules, and elements of the Inter- research laboratory modules, and elements of the Inter- research laboratory modules, and elements of the Inter- national Space Station. Processing activities begin years national Space Station. Processing activities begin years national Space Station. Processing activities begin years before a mission is scheduled to fly; the advance time before a mission is scheduled to fly; the advance time before a mission is scheduled to fly; the advance time depends on the mission’s complexity. depends on the mission’s complexity. depends on the mission’s complexity.

Boeing is pursuing NASA's Exploration Ground Launch Boeing is pursuing NASA's Exploration Ground Launch Boeing is pursuing NASA's Exploration Ground Launch Services (EGLS) contract at Kennedy Space Center. Services (EGLS) contract at Kennedy Space Center. Services (EGLS) contract at Kennedy Space Center. Contract award is anticipated in April 2010. The EGLS Contract award is anticipated in April 2010. The EGLS Contract award is anticipated in April 2010. The EGLS contractor will perform final assembly, test, integration, contractor will perform final assembly, test, integration, contractor will perform final assembly, test, integration, launch, and recovery of the Constellation Program’s flight launch, and recovery of the Constellation Program’s flight launch, and recovery of the Constellation Program’s flight elements. EGLS will support the Ares I crew launch vehicle, elements. EGLS will support the Ares I crew launch vehicle, elements. EGLS will support the Ares I crew launch vehicle, the Ares V cargo launch vehicle, the Orion crew explora- the Ares V cargo launch vehicle, the Orion crew explora- the Ares V cargo launch vehicle, the Orion crew explora- tion vehicle, and the Altair lunar lander, beginning with the tion vehicle, and the Altair lunar lander, beginning with the tion vehicle, and the Altair lunar lander, beginning with the Constellation ground systems activation and continuing Constellation ground systems activation and continuing Constellation ground systems activation and continuing through the ISS and lunar missions. For more information, through the ISS and lunar missions. For more information, through the ISS and lunar missions. For more information, visit the EGLS web site at http://www.boeing.com/defense- visit the EGLS web site at http://www.boeing.com/defense- visit the EGLS web site at http://www.boeing.com/defense- space/space/constellation_egls/index.html. space/space/constellation_egls/index.html. space/space/constellation_egls/index.html.

Gd-2 Gd-2 Gd-2 SPACE SHUTTLE FACTS SPACE SHUTTLE FACTS SPACE SHUTTLE FACTS

LENGTH LENGTH LENGTH System: 184.2 ft System: 184.2 ft System: 184.2 ft Orbiter: 122.17 ft Orbiter: 122.17 ft Orbiter: 122.17 ft External Tank: 153.8 ft External Tank: 153.8 ft External Tank: 153.8 ft Solid Rocket Boosters (SRBs): 149.16 ft Solid Rocket Boosters (SRBs): 149.16 ft Solid Rocket Boosters (SRBs): 149.16 ft HEIGHT HEIGHT HEIGHT System: 76.6 ft System: 76.6 ft System: 76.6 ft Orbiter: 56.58 ft Orbiter: 56.58 ft Orbiter: 56.58 ft WINGSPAN WINGSPAN WINGSPAN Orbiter: 78.06 ft Orbiter: 78.06 ft Orbiter: 78.06 ft WEIGHT WEIGHT WEIGHT Gross Lift-Off: 4,500,000 lb Gross Lift-Off: 4,500,000 lb Gross Lift-Off: 4,500,000 lb Orbiter Landing: Varies, dependent Orbiter Landing: Varies, dependent Orbiter Landing: Varies, dependent upon mission upon mission upon mission ORBITER DRY WEIGHT (WITH THREE ORBITER DRY WEIGHT (WITH THREE ORBITER DRY WEIGHT (WITH THREE SPACE SHUTTLE MAIN ENGINES) SPACE SHUTTLE MAIN ENGINES) SPACE SHUTTLE MAIN ENGINES) Discovery: 176,419 lb Discovery: 176,419 lb Discovery: 176,419 lb Atlantis: 176,413 lb Atlantis: 176,413 lb Atlantis: 176,413 lb Endeavour: 176,056 lb Endeavour: 176,056 lb Endeavour: 176,056 lb External Tank (Full): 1,668,500 lb External Tank (Full): 1,668,500 lb External Tank (Full): 1,668,500 lb External Tank (Inert): 58,500 lb External Tank (Inert): 58,500 lb External Tank (Inert): 58,500 lb SRBs (2), Each at Launch: 1,298,500 lb SRBs (2), Each at Launch: 1,298,500 lb SRBs (2), Each at Launch: 1,298,500 lb SRB Inert Weight, Each: 186,800 lb SRB Inert Weight, Each: 186,800 lb SRB Inert Weight, Each: 186,800 lb THRUST THRUST THRUST SRBs (2): SRBs (2): SRBs (2): 3,300,000 lb of thrust each in a vacuum 3,300,000 lb of thrust each in a vacuum 3,300,000 lb of thrust each in a vacuum Space Shuttle Main Engines (3): Space Shuttle Main Engines (3): Space Shuttle Main Engines (3): 418,000 lb of thrust each at sea level at 418,000 lb of thrust each at sea level at 418,000 lb of thrust each at sea level at 109 percent 109 percent 109 percent CARGO BAY CARGO BAY CARGO BAY Dimensions: Dimensions: Dimensions: 60-ft long, 15 ft in diameter 60-ft long, 15 ft in diameter 60-ft long, 15 ft in diameter Payloads: Payloads: Payloads: Unmanned spacecraft to fully equipped Unmanned spacecraft to fully equipped Unmanned spacecraft to fully equipped scientific laboratories and ISS elements scientific laboratories and ISS elements scientific laboratories and ISS elements PERFORMANCE PERFORMANCE PERFORMANCE Payload for 160 nmi Orbit Payload for 160 nmi Orbit Payload for 160 nmi Orbit Due East (28.5°)—Discovery, Due East (28.5°)—Discovery, Due East (28.5°)—Discovery, Atlantis, or Endeavour: 54,000 lb* Atlantis, or Endeavour: 54,000 lb* Atlantis, or Endeavour: 54,000 lb* High Inclination (51.6°)—Discovery, High Inclination (51.6°)—Discovery, High Inclination (51.6°)—Discovery, Atlantis, or Endeavour: 36,200 lb* Atlantis, or Endeavour: 36,200 lb* Atlantis, or Endeavour: 36,200 lb* (weights approximate) (weights approximate) (weights approximate)

*Includes: Managers’ reserve, payload attach hardware, *Includes: Managers’ reserve, payload attach hardware, *Includes: Managers’ reserve, payload attach hardware, and flight support equipment and flight support equipment and flight support equipment

Gd-3 Gd-3 Gd-3 Gd-4 Gd-4 Gd-4 56.58 ft 56.58 ft 56.58 ft

External External External Tank (ET) Tank (ET) Tank (ET) 27.6-ft 27.6-ft 27.6-ft Diameter Diameter Diameter

SRB Thrust SRB Thrust SRB Thrust Attachment Attachment Attachment

Solid Solid Solid Rocket Rocket Rocket Booster Booster Booster (SRB) (SRB) (SRB) 12.17-ft 12.17-ft 12.17-ft Diameter Diameter Diameter

Orbiter Orbiter Orbiter Length Length Length 122.17 ft 122.17 ft 122.17 ft

78.06 ft 78.06 ft 78.06 ft

Gd-5 Gd-5 Gd-5 Space Shuttle Main Engine Space Shuttle Main Engine Space Shuttle Main Engine The Space Shuttle Main Engines (SSMEs) are the most The Space Shuttle Main Engines (SSMEs) are the most The Space Shuttle Main Engines (SSMEs) are the most reliable and highly tested large rocket engines ever built. reliable and highly tested large rocket engines ever built. reliable and highly tested large rocket engines ever built. The SSMEs operate at greater temperature extremes than The SSMEs operate at greater temperature extremes than The SSMEs operate at greater temperature extremes than any mechanical system in common use today. At -423ºF, any mechanical system in common use today. At -423ºF, any mechanical system in common use today. At -423ºF, the engine’s fuel, liquefied hydrogen, is the second coldest the engine’s fuel, liquefied hydrogen, is the second coldest the engine’s fuel, liquefied hydrogen, is the second coldest liquid on Earth. When it and the liquid oxygen are combined liquid on Earth. When it and the liquid oxygen are combined liquid on Earth. When it and the liquid oxygen are combined and combusted, the temperature in the main combustion and combusted, the temperature in the main combustion and combusted, the temperature in the main combustion chamber is 6,000ºF, hotter than the boiling point of iron. chamber is 6,000ºF, hotter than the boiling point of iron. chamber is 6,000ºF, hotter than the boiling point of iron. One SSME generates enough thrust to maintain the flight One SSME generates enough thrust to maintain the flight One SSME generates enough thrust to maintain the flight of 2.5 Boeing 747s. Some 64,000 gallons of fuel are con- of 2.5 Boeing 747s. Some 64,000 gallons of fuel are con- of 2.5 Boeing 747s. Some 64,000 gallons of fuel are con- sumed by the main engines each minute. Even though an sumed by the main engines each minute. Even though an sumed by the main engines each minute. Even though an SSME weighs one-seventh as much as a locomotive en- SSME weighs one-seventh as much as a locomotive en- SSME weighs one-seventh as much as a locomotive en- gine, its high-pressure fuel pump alone delivers as much gine, its high-pressure fuel pump alone delivers as much gine, its high-pressure fuel pump alone delivers as much horsepower as 28 locomotives, while its high-pressure horsepower as 28 locomotives, while its high-pressure horsepower as 28 locomotives, while its high-pressure oxidizer pump delivers the equivalent horsepower of an oxidizer pump delivers the equivalent horsepower of an oxidizer pump delivers the equivalent horsepower of an additional 11 locomotives. additional 11 locomotives. additional 11 locomotives. The SSMEs are built by Pratt & Whitney Rocketdyne, a The SSMEs are built by Pratt & Whitney Rocketdyne, a The SSMEs are built by Pratt & Whitney Rocketdyne, a business unit of United Technologies. Development of the business unit of United Technologies. Development of the business unit of United Technologies. Development of the engines began in the early 1970s, and the engines first engines began in the early 1970s, and the engines first engines began in the early 1970s, and the engines first flew in 1981. Since that time, the SSME remains the only flew in 1981. Since that time, the SSME remains the only flew in 1981. Since that time, the SSME remains the only reusable large rocket engine rated for human space flight reusable large rocket engine rated for human space flight reusable large rocket engine rated for human space flight in the world, with several having logged more than 20 mis- in the world, with several having logged more than 20 mis- in the world, with several having logged more than 20 mis- sions. It is also the most efficient engine in the world, with sions. It is also the most efficient engine in the world, with sions. It is also the most efficient engine in the world, with an efficiency rating—or Isp—of 452.3 seconds. an efficiency rating—or Isp—of 452.3 seconds. an efficiency rating—or Isp—of 452.3 seconds. PERFORMANCE PERFORMANCE PERFORMANCE

BLOCK II SSME (FULL-POWER LEVEL) BLOCK II SSME (FULL-POWER LEVEL) BLOCK II SSME (FULL-POWER LEVEL)

MAXIMUM THRUST (109% POWER LEVEL) MAXIMUM THRUST (109% POWER LEVEL) MAXIMUM THRUST (109% POWER LEVEL) At Sea Level: 418,000 lb At Sea Level: 418,000 lb At Sea Level: 418,000 lb In Vacuum: 512,300 lb In Vacuum: 512,300 lb In Vacuum: 512,300 lb THROTTLE RANGE: 67–109 percent THROTTLE RANGE: 67–109 percent THROTTLE RANGE: 67–109 percent

PRESSURES PRESSURES PRESSURES Hydrogen Pump Discharge: 6,226 psia Hydrogen Pump Discharge: 6,226 psia Hydrogen Pump Discharge: 6,226 psia Oxygen Pump Discharge: 7,319 psia Oxygen Pump Discharge: 7,319 psia Oxygen Pump Discharge: 7,319 psia Chamber Pressure: 2,994 psia Chamber Pressure: 2,994 psia Chamber Pressure: 2,994 psia SPECIFIC IMPULSE (IN VACUUM): 452.3 sec SPECIFIC IMPULSE (IN VACUUM): 452.3 sec SPECIFIC IMPULSE (IN VACUUM): 452.3 sec

POWER OF HIGH-PRESSURE PUMPS POWER OF HIGH-PRESSURE PUMPS POWER OF HIGH-PRESSURE PUMPS Hydrogen: 69,452 HP Hydrogen: 69,452 HP Hydrogen: 69,452 HP Oxygen: 23,551 HP Oxygen: 23,551 HP Oxygen: 23,551 HP NOZZLE AREA RATIO: 69:1 NOZZLE AREA RATIO: 69:1 NOZZLE AREA RATIO: 69:1

WEIGHT: 7,774 lb WEIGHT: 7,774 lb WEIGHT: 7,774 lb

MIXTURE RATIO (OXIDIZER TO FUEL): 6.032:1 MIXTURE RATIO (OXIDIZER TO FUEL): 6.032:1 MIXTURE RATIO (OXIDIZER TO FUEL): 6.032:1

DIMENSIONS DIMENSIONS DIMENSIONS Length: 168 in. Length: 168 in. Length: 168 in. Width: 96 in. Width: 96 in. Width: 96 in.

Gd-6 Gd-6 Gd-6 Space Shuttle Main Engine Space Shuttle Main Engine Space Shuttle Main Engine

External Tank External Tank External Tank

The bright orange external tank—standing taller than a The bright orange external tank—standing taller than a The bright orange external tank—standing taller than a 15-story building with a length of 153.8 feet and as wide 15-story building with a length of 153.8 feet and as wide 15-story building with a length of 153.8 feet and as wide as a silo with a diameter of 27.6 feet—is the single largest as a silo with a diameter of 27.6 feet—is the single largest as a silo with a diameter of 27.6 feet—is the single largest component of the space shuttle and is not reusable. component of the space shuttle and is not reusable. component of the space shuttle and is not reusable.

The ET consists of three tanks: the forward liquid oxygen The ET consists of three tanks: the forward liquid oxygen The ET consists of three tanks: the forward liquid oxygen tank, the aft liquid hydrogen tank, and an unpressurized tank, the aft liquid hydrogen tank, and an unpressurized tank, the aft liquid hydrogen tank, and an unpressurized intertank that unites the two propellant tanks. Weighing intertank that unites the two propellant tanks. Weighing intertank that unites the two propellant tanks. Weighing 58,500 lb empty and 1,668,500 lb when filled with propel- 58,500 lb empty and 1,668,500 lb when filled with propel- 58,500 lb empty and 1,668,500 lb when filled with propel- lants, the ET supplies more than 535,000 gallons of liquid lants, the ET supplies more than 535,000 gallons of liquid lants, the ET supplies more than 535,000 gallons of liquid hydrogen and oxygen to the shuttle’s main engines. hydrogen and oxygen to the shuttle’s main engines. hydrogen and oxygen to the shuttle’s main engines.

The ET is primarily made of a lightweight aluminum-lithium The ET is primarily made of a lightweight aluminum-lithium The ET is primarily made of a lightweight aluminum-lithium alloy and consists of approximately 481,450 parts. If all alloy and consists of approximately 481,450 parts. If all alloy and consists of approximately 481,450 parts. If all the weld joints in the ET were laid out in a straight line, the weld joints in the ET were laid out in a straight line, the weld joints in the ET were laid out in a straight line, they would stretch more than half a mile. Despite its size, they would stretch more than half a mile. Despite its size, they would stretch more than half a mile. Despite its size, the aluminum skin of the tank is only 0.25-inch thick in the aluminum skin of the tank is only 0.25-inch thick in the aluminum skin of the tank is only 0.25-inch thick in most areas. most areas. most areas.

The ET is covered with a thermal protection system, or The ET is covered with a thermal protection system, or The ET is covered with a thermal protection system, or spray-on polyurethane-like foam insulation, which, if spray-on polyurethane-like foam insulation, which, if spray-on polyurethane-like foam insulation, which, if spread on the ground, would cover nearly two-thirds of spread on the ground, would cover nearly two-thirds of spread on the ground, would cover nearly two-thirds of an acre. The foam insulation on the majority of the tank an acre. The foam insulation on the majority of the tank an acre. The foam insulation on the majority of the tank is only 1-inch thick. is only 1-inch thick. is only 1-inch thick.

Gd-7 Gd-7 Gd-7 The closed-cell foam used on the ET was developed to The closed-cell foam used on the ET was developed to The closed-cell foam used on the ET was developed to keep the propellants that fuel the shuttle’s three main en- keep the propellants that fuel the shuttle’s three main en- keep the propellants that fuel the shuttle’s three main en- gines at optimum temperature. It keeps the shuttle’s liquid gines at optimum temperature. It keeps the shuttle’s liquid gines at optimum temperature. It keeps the shuttle’s liquid hydrogen fuel at -423ºF and the liquid oxygen tank at hydrogen fuel at -423ºF and the liquid oxygen tank at hydrogen fuel at -423ºF and the liquid oxygen tank at near -297ºF—even as the tank sits exposed to the Florida near -297ºF—even as the tank sits exposed to the Florida near -297ºF—even as the tank sits exposed to the Florida weather—while preventing a weather—while preventing a weather—while preventing a buildup of ice on the outside buildup of ice on the outside buildup of ice on the outside of the tank. of the tank. of the tank.

The retrofitted ET incorpo- The retrofitted ET incorpo- The retrofitted ET incorpo- rates design and process rates design and process rates design and process changes to increase safety changes to increase safety changes to increase safety and minimize the size and and minimize the size and and minimize the size and probability of debris gen- probability of debris gen- probability of debris gen- erated during launch and erated during launch and erated during launch and ascent. ascent. ascent.

The combined volume of the The combined volume of the The combined volume of the ET’s liquid hydrogen and ET’s liquid hydrogen and ET’s liquid hydrogen and liquid oxygen tanks is 73,600 liquid oxygen tanks is 73,600 liquid oxygen tanks is 73,600 cubic feet—equal to the cubic feet—equal to the cubic feet—equal to the volume of nearly six 1,600- volume of nearly six 1,600- volume of nearly six 1,600- square-foot homes. Loading square-foot homes. Loading square-foot homes. Loading of the propellant takes ap- of the propellant takes ap- of the propellant takes ap- proximately 3 hours. proximately 3 hours. proximately 3 hours.

During ascent, the ET sup- During ascent, the ET sup- During ascent, the ET sup- plies cryogenic propellants plies cryogenic propellants plies cryogenic propellants through 17-inch feedlines to through 17-inch feedlines to through 17-inch feedlines to the orbiter engines at a rate the orbiter engines at a rate the orbiter engines at a rate of 1,035 gallons per second. of 1,035 gallons per second. of 1,035 gallons per second. The ET absorbs most of The ET absorbs most of The ET absorbs most of the 7,000,000 lb of thrust the 7,000,000 lb of thrust the 7,000,000 lb of thrust exerted by the solid rocket exerted by the solid rocket exerted by the solid rocket boosters and the orbiter’s boosters and the orbiter’s boosters and the orbiter’s main engines. Within 8.5 main engines. Within 8.5 main engines. Within 8.5 minutes, the orbiter has minutes, the orbiter has minutes, the orbiter has reached space, traveling at reached space, traveling at reached space, traveling at a rate in excess of 17,500 a rate in excess of 17,500 a rate in excess of 17,500 mph. At that point, the ET mph. At that point, the ET mph. At that point, the ET separates from the orbiter separates from the orbiter separates from the orbiter and most of the tank disinte- and most of the tank disinte- and most of the tank disinte- grates upon reentry into the grates upon reentry into the grates upon reentry into the Earth's atmosphere. Earth's atmosphere. Earth's atmosphere.

The last flight tank to fly— The last flight tank to fly— The last flight tank to fly— ET-138—will be delivered to ET-138—will be delivered to ET-138—will be delivered to NASA in June 2010. ET-138 NASA in June 2010. ET-138 NASA in June 2010. ET-138 will be part of the space will be part of the space will be part of the space shuttle's final mission— shuttle's final mission— shuttle's final mission— STS-133—now targeted for STS-133—now targeted for STS-133—now targeted for launch in September 2010. External Tank launch in September 2010. External Tank launch in September 2010. External Tank Lockheed Martin Space Systems–Michoud Operations Lockheed Martin Space Systems–Michoud Operations Lockheed Martin Space Systems–Michoud Operations builds the space shuttle external tank at the NASA Michoud builds the space shuttle external tank at the NASA Michoud builds the space shuttle external tank at the NASA Michoud A s s e m b l y Fac ili t y in N e w O r l e a n s u n d e r c o nt rac t to t h e N A S A A s s e m b l y Fac ili t y in N e w O r l e a n s u n d e r c o nt rac t to t h e N A S A Assembly Facility in New Orleans under contract to the NASA Marshall Space Flight Center in Huntsville, Ala. Marshall Space Flight Center in Huntsville, Ala. Marshall Space Flight Center in Huntsville, Ala.

Gd-8 Gd-8 Gd-8 Solid Rocket Boosters Solid Rocket Boosters Solid Rocket Boosters The space shuttle’s two solid rocket boosters (SRBs), the The space shuttle’s two solid rocket boosters (SRBs), the The space shuttle’s two solid rocket boosters (SRBs), the first designed for refurbishment and reuse, are also the first designed for refurbishment and reuse, are also the first designed for refurbishment and reuse, are also the largest solid rockets ever built and the first to be flown on largest solid rockets ever built and the first to be flown on largest solid rockets ever built and the first to be flown on a manned spacecraft. a manned spacecraft. a manned spacecraft. The two SRBs generate a combined thrust of 6,600,000 The two SRBs generate a combined thrust of 6,600,000 The two SRBs generate a combined thrust of 6,600,000 lb, equivalent to 44,000,000 horsepower or 14,700 six-axle lb, equivalent to 44,000,000 horsepower or 14,700 six-axle lb, equivalent to 44,000,000 horsepower or 14,700 six-axle diesel locomotives or 400,000 subcompact cars. diesel locomotives or 400,000 subcompact cars. diesel locomotives or 400,000 subcompact cars. Each of the shuttle’s solid rocket boosters burns five tons Each of the shuttle’s solid rocket boosters burns five tons Each of the shuttle’s solid rocket boosters burns five tons of propellant per second, a total of 1,100,000 lb in 120 of propellant per second, a total of 1,100,000 lb in 120 of propellant per second, a total of 1,100,000 lb in 120 seconds. At liftoff, each SRB consumes 11,000 lb of fuel seconds. At liftoff, each SRB consumes 11,000 lb of fuel seconds. At liftoff, each SRB consumes 11,000 lb of fuel per second. That’s two million times the rate at which fuel per second. That’s two million times the rate at which fuel per second. That’s two million times the rate at which fuel is burned by the average family car. is burned by the average family car. is burned by the average family car. If their heat energy could be converted to electric power, If their heat energy could be converted to electric power, If their heat energy could be converted to electric power, two SRBs firing for 2 minutes would produce 2,200,000 two SRBs firing for 2 minutes would produce 2,200,000 two SRBs firing for 2 minutes would produce 2,200,000 kilowatt hours of power, enough to supply the entire power kilowatt hours of power, enough to supply the entire power kilowatt hours of power, enough to supply the entire power demand of 87,000 homes for a full day. demand of 87,000 homes for a full day. demand of 87,000 homes for a full day. The speed of the gases exiting the nozzle is more than The speed of the gases exiting the nozzle is more than The speed of the gases exiting the nozzle is more than 6,000 mph, about five times the speed of sound or three 6,000 mph, about five times the speed of sound or three 6,000 mph, about five times the speed of sound or three times the speed of a high-powered rifle bullet. The com- times the speed of a high-powered rifle bullet. The com- times the speed of a high-powered rifle bullet. The com- bustion gases in an SRB are at a temperature of 6,100ºF, bustion gases in an SRB are at a temperature of 6,100ºF, bustion gases in an SRB are at a temperature of 6,100ºF, two-thirds the temperature of the surface of the sun. While two-thirds the temperature of the surface of the sun. While two-thirds the temperature of the surface of the sun. While that temperature is hot enough to boil steel, special insula- that temperature is hot enough to boil steel, special insula- that temperature is hot enough to boil steel, special insula- tion inside the motor protects the steel case so well that tion inside the motor protects the steel case so well that tion inside the motor protects the steel case so well that the outside of the case reaches only about 130ºF. the outside of the case reaches only about 130ºF. the outside of the case reaches only about 130ºF. Each of the two SRBs has eight separation motors, which Each of the two SRBs has eight separation motors, which Each of the two SRBs has eight separation motors, which are small solid-fuel rocket motors designed to provide are small solid-fuel rocket motors designed to provide are small solid-fuel rocket motors designed to provide 24,000 lb of thrust each in less than 0.8 second. 24,000 lb of thrust each in less than 0.8 second. 24,000 lb of thrust each in less than 0.8 second. The two SRBs provide 80 percent of the thrust at liftoff The two SRBs provide 80 percent of the thrust at liftoff The two SRBs provide 80 percent of the thrust at liftoff and during first-stage ascent. and during first-stage ascent. and during first-stage ascent. After 2 minutes, at an altitude of about 24 miles, the After 2 minutes, at an altitude of about 24 miles, the After 2 minutes, at an altitude of about 24 miles, the boosters separate from the ET and descend by parachute boosters separate from the ET and descend by parachute boosters separate from the ET and descend by parachute approximately 141 miles downrange into the ocean, where approximately 141 miles downrange into the ocean, where approximately 141 miles downrange into the ocean, where they are collected for refurbishment and reuse. they are collected for refurbishment and reuse. they are collected for refurbishment and reuse. ATK Launch Systems builds the solid rocket boosters and ATK Launch Systems builds the solid rocket boosters and ATK Launch Systems builds the solid rocket boosters and separation motors at its facility in Promontory, Utah. separation motors at its facility in Promontory, Utah. separation motors at its facility in Promontory, Utah. Key Components: Key Components: Key Components: The Igniter: The igniter is mounted in the forward end of The Igniter: The igniter is mounted in the forward end of The Igniter: The igniter is mounted in the forward end of the SRB. It is approximately 48-inches long and 17 inches the SRB. It is approximately 48-inches long and 17 inches the SRB. It is approximately 48-inches long and 17 inches in diameter. Containing 134 lb of propellant, the igniter, in diameter. Containing 134 lb of propellant, the igniter, in diameter. Containing 134 lb of propellant, the igniter, when electrically activated, spreads flame down the entire when electrically activated, spreads flame down the entire when electrically activated, spreads flame down the entire length of the solid rocket booster. Approximately 0.34 sec- length of the solid rocket booster. Approximately 0.34 sec- length of the solid rocket booster. Approximately 0.34 sec- ond later, the space shuttle orbiter begins its ascent. ond later, the space shuttle orbiter begins its ascent. ond later, the space shuttle orbiter begins its ascent. The Motor Case: Consisting of 11 steel sections—nine The Motor Case: Consisting of 11 steel sections—nine The Motor Case: Consisting of 11 steel sections—nine cylinders, an aft dome, and a forward dome—joined cylinders, an aft dome, and a forward dome—joined cylinders, an aft dome, and a forward dome—joined tang to clevis and held together by load-bearing pins, the tang to clevis and held together by load-bearing pins, the tang to clevis and held together by load-bearing pins, the case is weld-free. Moreover, its segments are reusable— case is weld-free. Moreover, its segments are reusable— case is weld-free. Moreover, its segments are reusable— designed to perform safely and predictably for up to 20 designed to perform safely and predictably for up to 20 designed to perform safely and predictably for up to 20 launches. launches. launches.

Gd-9 Gd-9 Gd-9 Nose Cap Nose Cap Nose Cap (pilot and drogue (pilot and drogue (pilot and drogue parachutes) parachutes) parachutes) Forward Separation Forward Separation Forward Separation Motors (4) Motors (4) Motors (4) Three Main Parachutes Three Main Parachutes Three Main Parachutes Frustum Frustum Frustum Forward Skirt Forward Skirt Forward Skirt Avionics Avionics Avionics Igniter Igniter Igniter

Systems Tunnel Systems Tunnel Systems Tunnel Forward Forward Forward Segment Segment Segment With Igniter With Igniter With Igniter

Forward Systems Tunnel Forward Systems Tunnel Forward Systems Tunnel Center Center Center Segment Segment Segment

Systems Tunnel Systems Tunnel Systems Tunnel Aft Center Aft Center Aft Center Segment Segment Segment

Avionics Avionics Avionics External Tank Attach Ring External Tank Attach Ring External Tank Attach Ring Systems Tunnel Systems Tunnel Systems Tunnel Aft Segment Aft Segment Aft Segment With Nozzle With Nozzle With Nozzle Case Stiffener Rings (3) Case Stiffener Rings (3) Case Stiffener Rings (3) Gimbal Actuators (2) Gimbal Actuators (2) Gimbal Actuators (2) Nozzle Severance System Nozzle Severance System Nozzle Severance System Aft Exit Cone Aft Exit Cone Aft Exit Cone

Aft Separation Motors (4) Aft Separation Motors (4) Aft Separation Motors (4) Thrust Vector Control Thrust Vector Control Thrust Vector Control Systems (2) Systems (2) Systems (2) Aft Skirt Aft Skirt Aft Skirt

Solid Rocket Booster Solid Rocket Booster Solid Rocket Booster

Gd-10 Gd-10 Gd-10 The Propellant: When we speak of solid rocket boosters, The Propellant: When we speak of solid rocket boosters, The Propellant: When we speak of solid rocket boosters, we are referring to the propellant, which is a solid and has we are referring to the propellant, which is a solid and has we are referring to the propellant, which is a solid and has somewhat the same consistency as the eraser on a pencil. somewhat the same consistency as the eraser on a pencil. somewhat the same consistency as the eraser on a pencil. The solid propellant used to power the space shuttle is a The solid propellant used to power the space shuttle is a The solid propellant used to power the space shuttle is a composition of aluminum powder (the fuel), ammonium composition of aluminum powder (the fuel), ammonium composition of aluminum powder (the fuel), ammonium perchlorate (the oxidizer), HB polymer (the binder), a mea- perchlorate (the oxidizer), HB polymer (the binder), a mea- perchlorate (the oxidizer), HB polymer (the binder), a mea- sured amount of iron oxide to ensure the desired propellant sured amount of iron oxide to ensure the desired propellant sured amount of iron oxide to ensure the desired propellant burn rate, and an epoxy curing agent. burn rate, and an epoxy curing agent. burn rate, and an epoxy curing agent.

The Nozzle: The nozzle, the point of exit for the hot gases The Nozzle: The nozzle, the point of exit for the hot gases The Nozzle: The nozzle, the point of exit for the hot gases of combustion, is designed to move up to 8 degrees in of combustion, is designed to move up to 8 degrees in of combustion, is designed to move up to 8 degrees in any direction. This is made possible by the flexible bear- any direction. This is made possible by the flexible bear- any direction. This is made possible by the flexible bear- ing. This capability to direct the booster’s thrust is crucial ing. This capability to direct the booster’s thrust is crucial ing. This capability to direct the booster’s thrust is crucial to guiding the orbiter along its proper trajectory until the to guiding the orbiter along its proper trajectory until the to guiding the orbiter along its proper trajectory until the SRBs separate after liftoff. SRBs separate after liftoff. SRBs separate after liftoff.

Booster Separation Motor (BSM): Eight BSMs are used on Booster Separation Motor (BSM): Eight BSMs are used on Booster Separation Motor (BSM): Eight BSMs are used on each SRB; four motors are located on the forward section, each SRB; four motors are located on the forward section, each SRB; four motors are located on the forward section, and four are located on the aft skirt. The motors are fired and four are located on the aft skirt. The motors are fired and four are located on the aft skirt. The motors are fired after 2 minutes of flight to jettison the boosters away from after 2 minutes of flight to jettison the boosters away from after 2 minutes of flight to jettison the boosters away from the orbiter and external tank, allowing them to continue the orbiter and external tank, allowing them to continue the orbiter and external tank, allowing them to continue their flight into space. their flight into space. their flight into space.

Gd-11 Gd-11 Gd-11 Space Shuttle Weather Launch Commit Criteria Space Shuttle Weather Launch Commit Criteria Space Shuttle Weather Launch Commit Criteria The launch weather guidelines involving the space shuttle The launch weather guidelines involving the space shuttle The launch weather guidelines involving the space shuttle and expendable rockets are similar in many areas, but a and expendable rockets are similar in many areas, but a and expendable rockets are similar in many areas, but a distinction is made for the individual characteristics of distinction is made for the individual characteristics of distinction is made for the individual characteristics of each. The criteria are broadly conservative and ensure each. The criteria are broadly conservative and ensure each. The criteria are broadly conservative and ensure avoidance of possibly adverse conditions. They are avoidance of possibly adverse conditions. They are avoidance of possibly adverse conditions. They are reviewed for each launch. reviewed for each launch. reviewed for each launch. Space shuttle weather forecasts are provided by the Space shuttle weather forecasts are provided by the Space shuttle weather forecasts are provided by the U.S. Air Force Range Weather Operations Facility at U.S. Air Force Range Weather Operations Facility at U.S. Air Force Range Weather Operations Facility at Cape Canaveral beginning at Launch minus 3 days in Cape Canaveral beginning at Launch minus 3 days in Cape Canaveral beginning at Launch minus 3 days in coordination with the NOAA National Weather Service coordination with the NOAA National Weather Service coordination with the NOAA National Weather Service Space Flight Meteorology Group (SMG) at Johnson Space Space Flight Meteorology Group (SMG) at Johnson Space Space Flight Meteorology Group (SMG) at Johnson Space Center in Houston. These include weather trends and Center in Houston. These include weather trends and Center in Houston. These include weather trends and their possible effects on launch day. A formal prelaunch their possible effects on launch day. A formal prelaunch their possible effects on launch day. A formal prelaunch weather briefing is held on Launch minus 2 days, which weather briefing is held on Launch minus 2 days, which weather briefing is held on Launch minus 2 days, which is a specific weather briefing for all areas of space shuttle is a specific weather briefing for all areas of space shuttle is a specific weather briefing for all areas of space shuttle launch operations. launch operations. launch operations. Launch weather forecasts, ground operations forecasts, Launch weather forecasts, ground operations forecasts, Launch weather forecasts, ground operations forecasts, and launch weather briefings for the Mission Management and launch weather briefings for the Mission Management and launch weather briefings for the Mission Management Team and the Space Shuttle Launch Director are prepared Team and the Space Shuttle Launch Director are prepared Team and the Space Shuttle Launch Director are prepared by the Range Weather Operations Facility. Forecasts that by the Range Weather Operations Facility. Forecasts that by the Range Weather Operations Facility. Forecasts that apply after launch are prepared by SMG. These include apply after launch are prepared by SMG. These include apply after launch are prepared by SMG. These include all emergency landing forecasts and the end-of-mission all emergency landing forecasts and the end-of-mission all emergency landing forecasts and the end-of-mission forecasts briefed by SMG to the astronauts, the Flight forecasts briefed by SMG to the astronauts, the Flight forecasts briefed by SMG to the astronauts, the Flight Director, and Mission Management Team. Director, and Mission Management Team. Director, and Mission Management Team. During the countdown, formal weather briefings occur During the countdown, formal weather briefings occur During the countdown, formal weather briefings occur approximately as follows: approximately as follows: approximately as follows: L-24 hr 0 min: Briefing for Flight Director and L-24 hr 0 min: Briefing for Flight Director and L-24 hr 0 min: Briefing for Flight Director and astronauts astronauts astronauts L-21 hr 0 min: Briefing for removal of Rotating L-21 hr 0 min: Briefing for removal of Rotating L-21 hr 0 min: Briefing for removal of Rotating Service Structure Service Structure Service Structure L-9 hr 00 min: Briefing for external tank fuel loading L-9 hr 00 min: Briefing for external tank fuel loading L-9 hr 00 min: Briefing for external tank fuel loading L-4 hr 30 min: Briefing for Space Shuttle L-4 hr 30 min: Briefing for Space Shuttle L-4 hr 30 min: Briefing for Space Shuttle Launch Director Launch Director Launch Director L-3 hr 55 min: Briefing for astronauts L-3 hr 55 min: Briefing for astronauts L-3 hr 55 min: Briefing for astronauts L-2 hr 10 min: Briefing for Flight Director L-2 hr 10 min: Briefing for Flight Director L-2 hr 10 min: Briefing for Flight Director L-0 hr 35 min: Briefing for launch and RTLS L-0 hr 35 min: Briefing for launch and RTLS L-0 hr 35 min: Briefing for launch and RTLS L-0 hr 13 min: Poll all weather constraints L-0 hr 13 min: Poll all weather constraints L-0 hr 13 min: Poll all weather constraints The basic weather launch commit criteria on the pad at The basic weather launch commit criteria on the pad at The basic weather launch commit criteria on the pad at liftoff must be: liftoff must be: liftoff must be: Temperature: Prior to external tank propellant loading, Temperature: Prior to external tank propellant loading, Temperature: Prior to external tank propellant loading, tanking will not begin if the 24-hour average temperature tanking will not begin if the 24-hour average temperature tanking will not begin if the 24-hour average temperature has been below 41ºF. has been below 41ºF. has been below 41ºF. Wind: Tanking will not begin if the wind is observed or Wind: Tanking will not begin if the wind is observed or Wind: Tanking will not begin if the wind is observed or forecast to exceed 42 knots for the next 3-hour period. forecast to exceed 42 knots for the next 3-hour period. forecast to exceed 42 knots for the next 3-hour period. Precipitation: None at the launch pad or within the flight Precipitation: None at the launch pad or within the flight Precipitation: None at the launch pad or within the flight path. path. path.

Gd-12 Gd-12 Gd-12 Lightning (and electric fields with triggering potential): Lightning (and electric fields with triggering potential): Lightning (and electric fields with triggering potential): Tanking will not begin if there is forecast to be greater than Tanking will not begin if there is forecast to be greater than Tanking will not begin if there is forecast to be greater than a 20% chance of lightning within 5 nmi of the launch pad a 20% chance of lightning within 5 nmi of the launch pad a 20% chance of lightning within 5 nmi of the launch pad during the first hour of tanking. There will be no launch if during the first hour of tanking. There will be no launch if during the first hour of tanking. There will be no launch if lightning has been detected within 10 nmi of the pad or lightning has been detected within 10 nmi of the pad or lightning has been detected within 10 nmi of the pad or the planned flight path within 30 minutes prior to launch the planned flight path within 30 minutes prior to launch the planned flight path within 30 minutes prior to launch or if lightning is observed and the cloud that produced or if lightning is observed and the cloud that produced or if lightning is observed and the cloud that produced the lightning is within 10 nmi of the flight path. the lightning is within 10 nmi of the flight path. the lightning is within 10 nmi of the flight path.

Clouds (types known to contain hazardous electric Clouds (types known to contain hazardous electric Clouds (types known to contain hazardous electric fields): fields): fields): – Do not launch if any part of the planned flight path is – Do not launch if any part of the planned flight path is – Do not launch if any part of the planned flight path is through a layer of clouds any part of which within 5 nmi through a layer of clouds any part of which within 5 nmi through a layer of clouds any part of which within 5 nmi is 4,500-feet thick or greater and the temperature of is 4,500-feet thick or greater and the temperature of is 4,500-feet thick or greater and the temperature of any part of the layer is between 32ºF and -4ºF. Launch any part of the layer is between 32ºF and -4ºF. Launch any part of the layer is between 32ºF and -4ºF. Launch may occur if the cloud layer is a cirrus-like cloud that may occur if the cloud layer is a cirrus-like cloud that may occur if the cloud layer is a cirrus-like cloud that has never been associated with convective clouds, is has never been associated with convective clouds, is has never been associated with convective clouds, is located entirely at temperatures of 5ºF or colder, and located entirely at temperatures of 5ºF or colder, and located entirely at temperatures of 5ºF or colder, and shows no evidence of containing water droplets. shows no evidence of containing water droplets. shows no evidence of containing water droplets. – Do not launch through cumulus-type clouds with tops – Do not launch through cumulus-type clouds with tops – Do not launch through cumulus-type clouds with tops higher than the 41ºF temperature level. Launch may higher than the 41ºF temperature level. Launch may higher than the 41ºF temperature level. Launch may occur through clouds as cold as 23ºF if the cloud is occur through clouds as cold as 23ºF if the cloud is occur through clouds as cold as 23ºF if the cloud is not producing precipitation and all field mills within 5 not producing precipitation and all field mills within 5 not producing precipitation and all field mills within 5 nmi of the flight path and at least one field mill within nmi of the flight path and at least one field mill within nmi of the flight path and at least one field mill within 2 nmi of the cloud center read between -100 V/m and 2 nmi of the cloud center read between -100 V/m and 2 nmi of the cloud center read between -100 V/m and +500 V/m. +500 V/m. +500 V/m. – Do not launch (1) through or within 5 nmi of the nearest – Do not launch (1) through or within 5 nmi of the nearest – Do not launch (1) through or within 5 nmi of the nearest edge of cumulus-type clouds with tops higher than the edge of cumulus-type clouds with tops higher than the edge of cumulus-type clouds with tops higher than the 14ºF level; (2) through or within 10 nmi of the nearest 14ºF level; (2) through or within 10 nmi of the nearest 14ºF level; (2) through or within 10 nmi of the nearest edge of cumulus clouds with tops higher than the -4ºF edge of cumulus clouds with tops higher than the -4ºF edge of cumulus clouds with tops higher than the -4ºF level. level. level. – Do not launch if the flight path is through any nontrans- – Do not launch if the flight path is through any nontrans- – Do not launch if the flight path is through any nontrans- parent clouds that extend to altitudes at or above the parent clouds that extend to altitudes at or above the parent clouds that extend to altitudes at or above the 32ºF level that are associated with disturbed weather 32ºF level that are associated with disturbed weather 32ºF level that are associated with disturbed weather producing moderate or greater precipitation, or melting producing moderate or greater precipitation, or melting producing moderate or greater precipitation, or melting precipitation, within 5 nmi of the flight path. precipitation, within 5 nmi of the flight path. precipitation, within 5 nmi of the flight path. – Do not launch through an attached anvil cloud. If light- – Do not launch through an attached anvil cloud. If light- – Do not launch through an attached anvil cloud. If light- ning occurs in the anvil or the associated main cloud, ning occurs in the anvil or the associated main cloud, ning occurs in the anvil or the associated main cloud, do not launch within 10 nmi for the first 30 minutes after do not launch within 10 nmi for the first 30 minutes after do not launch within 10 nmi for the first 30 minutes after lightning is observed, or within 5 nmi from 30 minutes lightning is observed, or within 5 nmi from 30 minutes lightning is observed, or within 5 nmi from 30 minutes to 3 hours after lightning is observed. to 3 hours after lightning is observed. to 3 hours after lightning is observed. – Do not launch if the flight path will carry the vehicle – Do not launch if the flight path will carry the vehicle – Do not launch if the flight path will carry the vehicle a. Through nontransparent parts of a detached anvil a. Through nontransparent parts of a detached anvil a. Through nontransparent parts of a detached anvil for the first 3 hours after the anvil detaches from for the first 3 hours after the anvil detaches from for the first 3 hours after the anvil detaches from the parent cloud, or the first 4 hours after the last the parent cloud, or the first 4 hours after the last the parent cloud, or the first 4 hours after the last lightning occurs in the detached anvil. lightning occurs in the detached anvil. lightning occurs in the detached anvil. b. Within 10 nmi of nontransparent parts of a detached b. Within 10 nmi of nontransparent parts of a detached b. Within 10 nmi of nontransparent parts of a detached anvil for the first 30 minutes after the time of the last anvil for the first 30 minutes after the time of the last anvil for the first 30 minutes after the time of the last lightning in the parent or anvil cloud before detach- lightning in the parent or anvil cloud before detach- lightning in the parent or anvil cloud before detach- ment, or the detached anvil after its detachment. ment, or the detached anvil after its detachment. ment, or the detached anvil after its detachment.

Gd-13 Gd-13 Gd-13 c. Within 5 nmi of nontransparent parts of a detached c. Within 5 nmi of nontransparent parts of a detached c. Within 5 nmi of nontransparent parts of a detached anvil for the first 3 hours after the time of the last anvil for the first 3 hours after the time of the last anvil for the first 3 hours after the time of the last lightning in the parent or anvil cloud before detach- lightning in the parent or anvil cloud before detach- lightning in the parent or anvil cloud before detach- ment, or the detached anvil after detachment, unless ment, or the detached anvil after detachment, unless ment, or the detached anvil after detachment, unless there is a field mill within 5 nmi of the detached anvil there is a field mill within 5 nmi of the detached anvil there is a field mill within 5 nmi of the detached anvil reading less than 1,000 V/m for the last 15 minutes reading less than 1,000 V/m for the last 15 minutes reading less than 1,000 V/m for the last 15 minutes and a maximum radar returns from any part of the and a maximum radar returns from any part of the and a maximum radar returns from any part of the detached anvil within 5 nmi of the flight path have detached anvil within 5 nmi of the flight path have detached anvil within 5 nmi of the flight path have been less than 10 dBZ (light rain) for 15 minutes. been less than 10 dBZ (light rain) for 15 minutes. been less than 10 dBZ (light rain) for 15 minutes. – Do not launch if the flight path will carry the vehicle – Do not launch if the flight path will carry the vehicle – Do not launch if the flight path will carry the vehicle through a thunderstorm or cumulonimbus debris cloud through a thunderstorm or cumulonimbus debris cloud through a thunderstorm or cumulonimbus debris cloud that is not transparent and less than 3 hours old. Launch that is not transparent and less than 3 hours old. Launch that is not transparent and less than 3 hours old. Launch may not occur within 5 nmi of these debris clouds un- may not occur within 5 nmi of these debris clouds un- may not occur within 5 nmi of these debris clouds un- less (1) for 15 minutes preceding launch there is at least less (1) for 15 minutes preceding launch there is at least less (1) for 15 minutes preceding launch there is at least one working field mill within 5 nmi of the debris cloud; one working field mill within 5 nmi of the debris cloud; one working field mill within 5 nmi of the debris cloud; (2) all electric field mill readings are between -1 kV and (2) all electric field mill readings are between -1 kV and (2) all electric field mill readings are between -1 kV and +1 kV per meter within 5 nmi of the flight path; (3) no +1 kV per meter within 5 nmi of the flight path; (3) no +1 kV per meter within 5 nmi of the flight path; (3) no precipitation has been detected in the debris cloud (less precipitation has been detected in the debris cloud (less precipitation has been detected in the debris cloud (less than 10 dBZ by radar) within 5 nmi of the flight path. than 10 dBZ by radar) within 5 nmi of the flight path. than 10 dBZ by radar) within 5 nmi of the flight path. – Do not launch if the flight path will carry the vehicle – Do not launch if the flight path will carry the vehicle – Do not launch if the flight path will carry the vehicle through any cumulus cloud that has developed from a through any cumulus cloud that has developed from a through any cumulus cloud that has developed from a smoke plume while the cloud is attached to the plume, smoke plume while the cloud is attached to the plume, smoke plume while the cloud is attached to the plume, or for the first 60 minutes after the cumulus cloud de- or for the first 60 minutes after the cumulus cloud de- or for the first 60 minutes after the cumulus cloud de- taches from the smoke plume. taches from the smoke plume. taches from the smoke plume. To learn more about space shuttle weather launch crite- To learn more about space shuttle weather launch crite- To learn more about space shuttle weather launch crite- ria, go to NASA’s web site at http://www-pao.ksc.nasa. ria, go to NASA’s web site at http://www-pao.ksc.nasa. ria, go to NASA’s web site at http://www-pao.ksc.nasa. gov/kscpao/release/2002/92-02.htm. gov/kscpao/release/2002/92-02.htm. gov/kscpao/release/2002/92-02.htm.

Gd-14 Gd-14 Gd-14 Shuttle Carrier Aircraft Shuttle Carrier Aircraft Shuttle Carrier Aircraft When a space shuttle mission is nearing completion, ap- When a space shuttle mission is nearing completion, ap- When a space shuttle mission is nearing completion, ap- proximately 100 people are on standby at Dryden Flight proximately 100 people are on standby at Dryden Flight proximately 100 people are on standby at Dryden Flight Research Center (DFRC), located inside Edwards Air Force Research Center (DFRC), located inside Edwards Air Force Research Center (DFRC), located inside Edwards Air Force Base (EAFB) in California, just in case landing in Florida is Base (EAFB) in California, just in case landing in Florida is Base (EAFB) in California, just in case landing in Florida is not an option. Approximately 40 percent of the space shuttle not an option. Approximately 40 percent of the space shuttle not an option. Approximately 40 percent of the space shuttle missions have concluded their journeys in California. missions have concluded their journeys in California. missions have concluded their journeys in California. The shuttle is then ferried home to the launch complex The shuttle is then ferried home to the launch complex The shuttle is then ferried home to the launch complex at KSC atop a modified 747 aircraft, known as a Shuttle at KSC atop a modified 747 aircraft, known as a Shuttle at KSC atop a modified 747 aircraft, known as a Shuttle Carrier Aircraft (SCA). Carrier Aircraft (SCA). Carrier Aircraft (SCA).

Space shuttle Atlantis atop an SCA returns to KSC. Space shuttle Atlantis atop an SCA returns to KSC. Space shuttle Atlantis atop an SCA returns to KSC.

At EAFB, the space shuttle hanger, located near the At EAFB, the space shuttle hanger, located near the At EAFB, the space shuttle hanger, located near the Mate-Demate Device (MDD), is a single-bay, 25,000- Mate-Demate Device (MDD), is a single-bay, 25,000- Mate-Demate Device (MDD), is a single-bay, 25,000- square-foot structure that is 170-feet deep, 140-feet wide, square-foot structure that is 170-feet deep, 140-feet wide, square-foot structure that is 170-feet deep, 140-feet wide, and 80-feet high. A concrete tow-way connects the space and 80-feet high. A concrete tow-way connects the space and 80-feet high. A concrete tow-way connects the space shuttle hangar and the MDD with the aircraft ramp at the shuttle hangar and the MDD with the aircraft ramp at the shuttle hangar and the MDD with the aircraft ramp at the main Dryden complex and with the taxiway extending onto main Dryden complex and with the taxiway extending onto main Dryden complex and with the taxiway extending onto the EAFB flightline and runway network. the EAFB flightline and runway network. the EAFB flightline and runway network. The orbiter must be placed on top of the SCA by the The orbiter must be placed on top of the SCA by the The orbiter must be placed on top of the SCA by the MDD, a large gantry-like structure that hoists the orbiter MDD, a large gantry-like structure that hoists the orbiter MDD, a large gantry-like structure that hoists the orbiter off the ground for postflight servicing or mates it with the off the ground for postflight servicing or mates it with the off the ground for postflight servicing or mates it with the SCA for the ferry flight. Boeing has developed top-level SCA for the ferry flight. Boeing has developed top-level SCA for the ferry flight. Boeing has developed top-level procedures, specifications, and drawings for attaching procedures, specifications, and drawings for attaching procedures, specifications, and drawings for attaching the orbiter on top of the 747 using the MDD. the orbiter on top of the 747 using the MDD. the orbiter on top of the 747 using the MDD. The MDD facility consists of two 100-foot towers with The MDD facility consists of two 100-foot towers with The MDD facility consists of two 100-foot towers with stationary work platforms at the 20-, 40-, 60-, and 80-foot stationary work platforms at the 20-, 40-, 60-, and 80-foot stationary work platforms at the 20-, 40-, 60-, and 80-foot levels on each tower and a horizontal structure mounted levels on each tower and a horizontal structure mounted levels on each tower and a horizontal structure mounted at the 80-foot level between the two towers. The horizontal at the 80-foot level between the two towers. The horizontal at the 80-foot level between the two towers. The horizontal unit cantilevers 70 feet out from the main tower units and unit cantilevers 70 feet out from the main tower units and unit cantilevers 70 feet out from the main tower units and controls and guides a large lift beam that attaches to the controls and guides a large lift beam that attaches to the controls and guides a large lift beam that attaches to the orbiter to raise and lower it. orbiter to raise and lower it. orbiter to raise and lower it. Three large hoists are used to raise and lower the lift Three large hoists are used to raise and lower the lift Three large hoists are used to raise and lower the lift beam. Two of the hoists are connected to the aft portion beam. Two of the hoists are connected to the aft portion beam. Two of the hoists are connected to the aft portion of the lift beam, and one hoist is attached to the beam's of the lift beam, and one hoist is attached to the beam's of the lift beam, and one hoist is attached to the beam's forward section. The three hoists operate simultaneously forward section. The three hoists operate simultaneously forward section. The three hoists operate simultaneously in the hoisting process. Operating together, the total lifting in the hoisting process. Operating together, the total lifting in the hoisting process. Operating together, the total lifting capacity of the three units is 240,000 lb. capacity of the three units is 240,000 lb. capacity of the three units is 240,000 lb.

Gd-15 Gd-15 Gd-15 The process of raising the orbiter, sliding in the 747, and The process of raising the orbiter, sliding in the 747, and The process of raising the orbiter, sliding in the 747, and then lowering the orbiter onto the aircraft is a slow one. then lowering the orbiter onto the aircraft is a slow one. then lowering the orbiter onto the aircraft is a slow one. Three struts with associated interior structural strength- Three struts with associated interior structural strength- Three struts with associated interior structural strength- ening protrude from the top of the fuselage on which the ening protrude from the top of the fuselage on which the ening protrude from the top of the fuselage on which the orbiter is attached, two aft and one in front, similar to the orbiter is attached, two aft and one in front, similar to the orbiter is attached, two aft and one in front, similar to the attach points used for the external tank. The team also attach points used for the external tank. The team also attach points used for the external tank. The team also inspects the landing gear, external tank disconnect doors, inspects the landing gear, external tank disconnect doors, inspects the landing gear, external tank disconnect doors, payload bay doors, drag chute, and the airframe. payload bay doors, drag chute, and the airframe. payload bay doors, drag chute, and the airframe.

At EAFB, the SCA is towed beneath the space shuttle, At EAFB, the SCA is towed beneath the space shuttle, At EAFB, the SCA is towed beneath the space shuttle, suspended in the MDD. suspended in the MDD. suspended in the MDD.

Ferry flight unique hardware consists of a 10,000-lb aero- Ferry flight unique hardware consists of a 10,000-lb aero- Ferry flight unique hardware consists of a 10,000-lb aero- dynamic tailcone installed over the orbiter’s main engine dynamic tailcone installed over the orbiter’s main engine dynamic tailcone installed over the orbiter’s main engine nozzles, carrier panels, external tank ferry flight doors, nozzles, carrier panels, external tank ferry flight doors, nozzles, carrier panels, external tank ferry flight doors, cap and plug sets, auxiliary power unit vent drain line cap and plug sets, auxiliary power unit vent drain line cap and plug sets, auxiliary power unit vent drain line covers, and other items that are installed on the orbiter. covers, and other items that are installed on the orbiter. covers, and other items that are installed on the orbiter. The tailcone and vertical stabilizers on the tail reduce The tailcone and vertical stabilizers on the tail reduce The tailcone and vertical stabilizers on the tail reduce aerodynamic drag and smooth out the airflow over the aerodynamic drag and smooth out the airflow over the aerodynamic drag and smooth out the airflow over the orbiter during the ferry flight. orbiter during the ferry flight. orbiter during the ferry flight. The 747 has been extensively modified, all for the sake of The 747 has been extensively modified, all for the sake of The 747 has been extensively modified, all for the sake of reducing weight. The passenger area has been stripped of reducing weight. The passenger area has been stripped of reducing weight. The passenger area has been stripped of all galleys, carpeting, and even some inside temperature all galleys, carpeting, and even some inside temperature all galleys, carpeting, and even some inside temperature ductwork. The plane still weighs more than 300,000 lb, ductwork. The plane still weighs more than 300,000 lb, ductwork. The plane still weighs more than 300,000 lb, and the orbiter atop weighs 176,000 lb or more, depending and the orbiter atop weighs 176,000 lb or more, depending and the orbiter atop weighs 176,000 lb or more, depending on any onboard payload. on any onboard payload. on any onboard payload. During a normal flight, the SCA might use 20,000 lb of fuel During a normal flight, the SCA might use 20,000 lb of fuel During a normal flight, the SCA might use 20,000 lb of fuel an hour; with an orbiter on its back, that number doubles. an hour; with an orbiter on its back, that number doubles. an hour; with an orbiter on its back, that number doubles.

Gd-16 Gd-16 Gd-16 Each time NASA needs to ferry an orbiter from California Each time NASA needs to ferry an orbiter from California Each time NASA needs to ferry an orbiter from California to Florida, it costs the agency approximately $1.8 million. to Florida, it costs the agency approximately $1.8 million. to Florida, it costs the agency approximately $1.8 million. The vast majority of that cost is fuel for the 747, which The vast majority of that cost is fuel for the 747, which The vast majority of that cost is fuel for the 747, which burns one gallon for every plane length it flies. burns one gallon for every plane length it flies. burns one gallon for every plane length it flies. During the flight, only four people are on board: the crew During the flight, only four people are on board: the crew During the flight, only four people are on board: the crew of two pilots and two engineers. The small team forming of two pilots and two engineers. The small team forming of two pilots and two engineers. The small team forming SCA crews includes specially trained pilots and flight SCA crews includes specially trained pilots and flight SCA crews includes specially trained pilots and flight engineers who are former military aviators qualified to fly engineers who are former military aviators qualified to fly engineers who are former military aviators qualified to fly several types of aircraft. several types of aircraft. several types of aircraft. In addition, a “Pathfinder” aircraft, usually a U.S. Air Force In addition, a “Pathfinder” aircraft, usually a U.S. Air Force In addition, a “Pathfinder” aircraft, usually a U.S. Air Force cargo plane, flies 100 miles ahead of the SCA, carrying cargo plane, flies 100 miles ahead of the SCA, carrying cargo plane, flies 100 miles ahead of the SCA, carrying weather officers and space shuttle personnel from KSC. weather officers and space shuttle personnel from KSC. weather officers and space shuttle personnel from KSC. Also on board is an experienced SCA pilot, whose exper- Also on board is an experienced SCA pilot, whose exper- Also on board is an experienced SCA pilot, whose exper- tise helps the ferry flight crew keep to the safest route. tise helps the ferry flight crew keep to the safest route. tise helps the ferry flight crew keep to the safest route. Flying with the additional drag and weight of the orbiter Flying with the additional drag and weight of the orbiter Flying with the additional drag and weight of the orbiter imposes altitude and fuel restrictions as well. The range imposes altitude and fuel restrictions as well. The range imposes altitude and fuel restrictions as well. The range is reduced to 1,000 nmi compared to an unladen range is reduced to 1,000 nmi compared to an unladen range is reduced to 1,000 nmi compared to an unladen range of 5,500 nmi, requiring an SCA to stop several times to of 5,500 nmi, requiring an SCA to stop several times to of 5,500 nmi, requiring an SCA to stop several times to refuel on the 2,500-mile cross-country flight. The SCA has refuel on the 2,500-mile cross-country flight. The SCA has refuel on the 2,500-mile cross-country flight. The SCA has an altitude ceiling of 15,000 feet and a maximum cruise an altitude ceiling of 15,000 feet and a maximum cruise an altitude ceiling of 15,000 feet and a maximum cruise speed of Mach 0.6 with the orbiter attached. speed of Mach 0.6 with the orbiter attached. speed of Mach 0.6 with the orbiter attached. Perhaps the biggest challenge the crew faces during Perhaps the biggest challenge the crew faces during Perhaps the biggest challenge the crew faces during a ferry flight is the weather. The orbiter tiles cannot be a ferry flight is the weather. The orbiter tiles cannot be a ferry flight is the weather. The orbiter tiles cannot be exposed to moisture, turbulence, or temperatures below exposed to moisture, turbulence, or temperatures below exposed to moisture, turbulence, or temperatures below 15°F, and these restrictions determine the SCA’s flight 15°F, and these restrictions determine the SCA’s flight 15°F, and these restrictions determine the SCA’s flight path and altitude. To meet these conditions in the winter path and altitude. To meet these conditions in the winter path and altitude. To meet these conditions in the winter months, the SCA sometimes flies as low as 10,000 feet. months, the SCA sometimes flies as low as 10,000 feet. months, the SCA sometimes flies as low as 10,000 feet.

A space shuttle atop an SCA is towed toward the MDD at A space shuttle atop an SCA is towed toward the MDD at A space shuttle atop an SCA is towed toward the MDD at the Shuttle Landing Facility at KSC. Once underneath the the Shuttle Landing Facility at KSC. Once underneath the the Shuttle Landing Facility at KSC. Once underneath the device, a hoist will lift the space shuttle from the back of device, a hoist will lift the space shuttle from the back of device, a hoist will lift the space shuttle from the back of the SCA and place it on the ground. the SCA and place it on the ground. the SCA and place it on the ground.

Gd-17 Gd-17 Gd-17 Shuttle Amazing Facts Shuttle Amazing Facts Shuttle Amazing Facts The space shuttle has more than 2,500,000 parts, includ- The space shuttle has more than 2,500,000 parts, includ- The space shuttle has more than 2,500,000 parts, includ- ing about 170 miles of wire, more than 1,060 plumbing ing about 170 miles of wire, more than 1,060 plumbing ing about 170 miles of wire, more than 1,060 plumbing valves and connections, about 1,440 circuit breakers, and valves and connections, about 1,440 circuit breakers, and valves and connections, about 1,440 circuit breakers, and more than 24,000 insulating tiles and thermal blankets. It more than 24,000 insulating tiles and thermal blankets. It more than 24,000 insulating tiles and thermal blankets. It is the most complex machine ever built. is the most complex machine ever built. is the most complex machine ever built.

Although it weighs more than 4,500,000 lb at launch, the Although it weighs more than 4,500,000 lb at launch, the Although it weighs more than 4,500,000 lb at launch, the space shuttle accelerates from zero to about nine times space shuttle accelerates from zero to about nine times space shuttle accelerates from zero to about nine times as fast as a rifle bullet, or more than 17,500 mph, to at- as fast as a rifle bullet, or more than 17,500 mph, to at- as fast as a rifle bullet, or more than 17,500 mph, to at- tain Earth orbit in less than 9 minutes, during which time tain Earth orbit in less than 9 minutes, during which time tain Earth orbit in less than 9 minutes, during which time more than 3,500,000 lb of propellants are completely more than 3,500,000 lb of propellants are completely more than 3,500,000 lb of propellants are completely consumed. The shuttle breaks the sound barrier 52 sec- consumed. The shuttle breaks the sound barrier 52 sec- consumed. The shuttle breaks the sound barrier 52 sec- onds into flight. onds into flight. onds into flight.

The orbiter, both the brains and heart of the Space Trans- The orbiter, both the brains and heart of the Space Trans- The orbiter, both the brains and heart of the Space Trans- portation System, is about the same size as a Boeing 737 portation System, is about the same size as a Boeing 737 portation System, is about the same size as a Boeing 737 aircraft. The cargo bay measures 60 feet by 15 feet in aircraft. The cargo bay measures 60 feet by 15 feet in aircraft. The cargo bay measures 60 feet by 15 feet in diameter and can carry cargo up to 65,000 lb. diameter and can carry cargo up to 65,000 lb. diameter and can carry cargo up to 65,000 lb.

The shuttle’s 24,000 individual tiles are made primarily The shuttle’s 24,000 individual tiles are made primarily The shuttle’s 24,000 individual tiles are made primarily of pure sand silicate fibers, mixed with a ceramic binder. of pure sand silicate fibers, mixed with a ceramic binder. of pure sand silicate fibers, mixed with a ceramic binder. Incredibly lightweight and about the same density as balsa Incredibly lightweight and about the same density as balsa Incredibly lightweight and about the same density as balsa wood, they dissipate the heat so quickly that a white-hot wood, they dissipate the heat so quickly that a white-hot wood, they dissipate the heat so quickly that a white-hot tile with a temperature of 2,300ºF can be taken from an tile with a temperature of 2,300ºF can be taken from an tile with a temperature of 2,300ºF can be taken from an oven and held in bare hands without injury. oven and held in bare hands without injury. oven and held in bare hands without injury.

Two orbital maneuvering system (OMS) engines, mounted Two orbital maneuvering system (OMS) engines, mounted Two orbital maneuvering system (OMS) engines, mounted on either side of the upper aft fuselage, provide thrust for on either side of the upper aft fuselage, provide thrust for on either side of the upper aft fuselage, provide thrust for major orbital changes. For more exacting motions in orbit, major orbital changes. For more exacting motions in orbit, major orbital changes. For more exacting motions in orbit, 44 small rocket engines, clustered on the shuttle’s nose 44 small rocket engines, clustered on the shuttle’s nose 44 small rocket engines, clustered on the shuttle’s nose and on either side of the tail, are used. Together, they are and on either side of the tail, are used. Together, they are and on either side of the tail, are used. Together, they are known as the reaction control system. known as the reaction control system. known as the reaction control system.

Temperatures experienced by the space shuttle range Temperatures experienced by the space shuttle range Temperatures experienced by the space shuttle range from as low as -250°F in space to as high as 3,000ºF from as low as -250°F in space to as high as 3,000ºF from as low as -250°F in space to as high as 3,000ºF during re-entry into the Earth’s atmosphere while traveling during re-entry into the Earth’s atmosphere while traveling during re-entry into the Earth’s atmosphere while traveling more than 17,000 mph. more than 17,000 mph. more than 17,000 mph.

At 149-feet, 1.6-inches tall, the solid rocket booster is only At 149-feet, 1.6-inches tall, the solid rocket booster is only At 149-feet, 1.6-inches tall, the solid rocket booster is only 2 feet shorter than the Statue of Liberty. But each 700-ton 2 feet shorter than the Statue of Liberty. But each 700-ton 2 feet shorter than the Statue of Liberty. But each 700-ton loaded booster weighs more than three times as much as loaded booster weighs more than three times as much as loaded booster weighs more than three times as much as the famous statue. The SRBs, which burn solid propellant, the famous statue. The SRBs, which burn solid propellant, the famous statue. The SRBs, which burn solid propellant, provide more than 70 percent of the space shuttle's thrust provide more than 70 percent of the space shuttle's thrust provide more than 70 percent of the space shuttle's thrust during the first 2 minutes of ascent. during the first 2 minutes of ascent. during the first 2 minutes of ascent.

The 15-story-tall, rust-colored external tank is the only The 15-story-tall, rust-colored external tank is the only The 15-story-tall, rust-colored external tank is the only shuttle element that isn’t reused. Despite its size, the shuttle element that isn’t reused. Despite its size, the shuttle element that isn’t reused. Despite its size, the aluminum skin of the tank is only 0.125-in. thick in most aluminum skin of the tank is only 0.125-in. thick in most aluminum skin of the tank is only 0.125-in. thick in most areas. It feeds more than 500,000 gallons of fuel to the areas. It feeds more than 500,000 gallons of fuel to the areas. It feeds more than 500,000 gallons of fuel to the shuttle’s main engines during launch at the rate of more shuttle’s main engines during launch at the rate of more shuttle’s main engines during launch at the rate of more than 1,000 gallons per second. than 1,000 gallons per second. than 1,000 gallons per second.

If the shuttle main engines pumped water instead of fuel, If the shuttle main engines pumped water instead of fuel, If the shuttle main engines pumped water instead of fuel, they would drain an average-size swimming pool in 25 they would drain an average-size swimming pool in 25 they would drain an average-size swimming pool in 25 seconds. seconds. seconds.

The two SRBs generate a combined thrust of 5.3 million The two SRBs generate a combined thrust of 5.3 million The two SRBs generate a combined thrust of 5.3 million lb, equivalent to 44 million horsepower. lb, equivalent to 44 million horsepower. lb, equivalent to 44 million horsepower.

Gd-18 Gd-18 Gd-18 Mini-Research Module 2 (MRM2) Final ISS Configuration Elements Currently on Orbit “Zvezda” Service SM MMOD Shields Module (SM) Elements Pending U.S. Shuttle Launch Elements Pending Russian Launch

Multi-Purpose Laboratory Module (MLM) European “Zarya” Functional Cargo Block (FGB) Robotic Arm

MLM Airlock Pressurized Heat Rejection Subsystem (HRS) Radiators P6 Truss Mating P4 Truss Segment Port Photovoltaic Arrays Solar Alpha Segment Mini-Research Adapter (PMA) 1 Rotary Joint Module 1 (MRM1) Special Purpose ESP3 Dexterous S0 Truss P5 Truss Segment Solar Alpha Manipulator Segment Rotary Joint ELC2 ELC3 “Dextre” P3 Truss Segment S6 Truss P1 Truss Segment Segment S5 Truss Segment Mobile Remote CSA Remote Servicer Base S3 Truss S1 Truss Manipulator System ExPRESS Logistics Segment System Carrier (ELC) 1 Segment Z1 Truss Segment Port Photovoltaic Radiators “Unity” Node 1 S4 Truss “Tranquility” Node 3 Segment “Quest” Starboard Photovoltaic Arrays Airlock Cupola JEM Experiment Logistics Module (ELM) Pressurized Section ESP2 External Stowage ELC4 Platform (ESP) 1 Pressurized JEM Remote Manipulator Starboard Photovoltaic Radiators Mating Adapter 3 “Destiny” U.S. Lab JEM Exposed Facility

“Columbus” “Kibo” Japanese Experiment Module (JEM) Pressurized Module European Lab “Harmony”Node 2 Pressurized Mating Adapter 2

Mini-Research Module 2 (MRM2) Final ISS Configuration Elements Currently on Orbit “Zvezda” Service SM MMOD Shields Module (SM) Elements Pending U.S. Shuttle Launch Elements Pending Russian Launch

Multi-Purpose Laboratory Module (MLM) European “Zarya” Functional Cargo Block (FGB) Robotic Arm

MLM Airlock Pressurized Heat Rejection Subsystem (HRS) Radiators P6 Truss Mating P4 Truss Segment Port Photovoltaic Arrays Solar Alpha Segment Mini-Research Adapter (PMA) 1 Rotary Joint Module 1 (MRM1) Special Purpose ESP3 Dexterous S0 Truss P5 Truss Segment Solar Alpha Manipulator Segment Rotary Joint ELC2 ELC3 “Dextre” P3 Truss Segment S6 Truss P1 Truss Segment Segment S5 Truss Segment Mobile Remote CSA Remote Servicer Base S3 Truss S1 Truss Manipulator System ExPRESS Logistics Segment System Carrier (ELC) 1 Segment Z1 Truss Segment Port Photovoltaic Radiators “Unity” Node 1 S4 Truss “Tranquility” Node 3 Segment “Quest” Starboard Photovoltaic Arrays Airlock Cupola JEM Experiment Logistics Module (ELM) Pressurized Section ESP2 External Stowage ELC4 Platform (ESP) 1 Pressurized JEM Remote Manipulator Starboard Photovoltaic Radiators Mating Adapter 3 “Destiny” U.S. Lab JEM Exposed Facility

“Columbus” “Kibo” Japanese Experiment Module (JEM) Pressurized Module European Lab “Harmony”Node 2 Pressurized Mating Adapter 2

Mini-Research Module 2 (MRM2) Final ISS Configuration Elements Currently on Orbit “Zvezda” Service SM MMOD Shields Module (SM) Elements Pending U.S. Shuttle Launch Elements Pending Russian Launch

Multi-Purpose Laboratory Module (MLM) European “Zarya” Functional Cargo Block (FGB) Robotic Arm

MLM Airlock Pressurized Heat Rejection Subsystem (HRS) Radiators P6 Truss Mating P4 Truss Segment Port Photovoltaic Arrays Solar Alpha Segment Mini-Research Adapter (PMA) 1 Rotary Joint Module 1 (MRM1) Special Purpose ESP3 Dexterous S0 Truss P5 Truss Segment Solar Alpha Manipulator Segment Rotary Joint ELC2 ELC3 “Dextre” P3 Truss Segment S6 Truss P1 Truss Segment Segment S5 Truss Segment Mobile Remote CSA Remote Servicer Base S3 Truss S1 Truss Manipulator System ExPRESS Logistics Segment System Carrier (ELC) 1 Segment Z1 Truss Segment Port Photovoltaic Radiators “Unity” Node 1 S4 Truss “Tranquility” Node 3 Segment “Quest” Starboard Photovoltaic Arrays Airlock Cupola JEM Experiment Logistics Module (ELM) Pressurized Section ESP2 External Stowage ELC4 Platform (ESP) 1 Pressurized JEM Remote Manipulator Starboard Photovoltaic Radiators Mating Adapter 3 “Destiny” U.S. Lab JEM Exposed Facility

“Columbus” “Kibo” Japanese Experiment Module (JEM) Pressurized Module European Lab “Harmony”Node 2 Pressurized Mating Adapter 2 BOEING AND THE INTERNATIONAL BOEING AND THE INTERNATIONAL BOEING AND THE INTERNATIONAL SPACE STATION SPACE STATION SPACE STATION

In 1993, NASA selected Boeing as the prime contractor In 1993, NASA selected Boeing as the prime contractor In 1993, NASA selected Boeing as the prime contractor for the International Space Station (ISS). As the prime for the International Space Station (ISS). As the prime for the International Space Station (ISS). As the prime contractor, Boeing directed an industry team comprising contractor, Boeing directed an industry team comprising contractor, Boeing directed an industry team comprising major U.S. aerospace companies and hundreds of smaller major U.S. aerospace companies and hundreds of smaller major U.S. aerospace companies and hundreds of smaller subcontractors. This collaboration guided the construc- subcontractors. This collaboration guided the construc- subcontractors. This collaboration guided the construc- tion, assembly, and utilization of the space station. tion, assembly, and utilization of the space station. tion, assembly, and utilization of the space station.

Exceeding the size of a football field, the ISS is the largest Exceeding the size of a football field, the ISS is the largest Exceeding the size of a football field, the ISS is the largest international space venture ever undertaken. Today, Boe- international space venture ever undertaken. Today, Boe- international space venture ever undertaken. Today, Boe- ing continues to provide sustaining engineering, payload ing continues to provide sustaining engineering, payload ing continues to provide sustaining engineering, payload integration, mission operation, and maintenance support, integration, mission operation, and maintenance support, integration, mission operation, and maintenance support, to ensure maximum utilization of the station as it nears to ensure maximum utilization of the station as it nears to ensure maximum utilization of the station as it nears assembly-complete. assembly-complete. assembly-complete.

Boeing Development and Production Boeing Development and Production Boeing Development and Production Boeing produced the space station’s pressurized U.S. Boeing produced the space station’s pressurized U.S. Boeing produced the space station’s pressurized U.S. modules, including Unity (Node 1), the U.S. Destiny Labo- modules, including Unity (Node 1), the U.S. Destiny Labo- modules, including Unity (Node 1), the U.S. Destiny Labo- ratory, and Quest (the ISS joint airlock). This production ratory, and Quest (the ISS joint airlock). This production ratory, and Quest (the ISS joint airlock). This production work was completed in Huntsville, Ala. The Huntsville team work was completed in Huntsville, Ala. The Huntsville team work was completed in Huntsville, Ala. The Huntsville team also designed the station’s environmental control and life also designed the station’s environmental control and life also designed the station’s environmental control and life support systems. Their contributions continued with the support systems. Their contributions continued with the support systems. Their contributions continued with the design of a common berthing mechanism. Used by all design of a common berthing mechanism. Used by all design of a common berthing mechanism. Used by all non-Russian pressurized modules, it allows the transfer non-Russian pressurized modules, it allows the transfer non-Russian pressurized modules, it allows the transfer of racks between non-Russian pressurized elements. The of racks between non-Russian pressurized elements. The of racks between non-Russian pressurized elements. The device is the largest berthing mechanism of its kind. device is the largest berthing mechanism of its kind. device is the largest berthing mechanism of its kind. Boeing was also tasked with the development of the end- Boeing was also tasked with the development of the end- Boeing was also tasked with the development of the end- to-end electrical power system architecture for the ISS. to-end electrical power system architecture for the ISS. to-end electrical power system architecture for the ISS. The system provides all user and housekeeping electrical The system provides all user and housekeeping electrical The system provides all user and housekeeping electrical power and is capable of expansion to accommodate new power and is capable of expansion to accommodate new power and is capable of expansion to accommodate new ISS components. ISS components. ISS components. Flexible and deployable, solar array wings provide power Flexible and deployable, solar array wings provide power Flexible and deployable, solar array wings provide power to the space station. Each wing consists of two blanket to the space station. Each wing consists of two blanket to the space station. Each wing consists of two blanket assemblies covered with solar cells. Following deploy- assemblies covered with solar cells. Following deploy- assemblies covered with solar cells. Following deploy- ment, each pair of blankets is supported by an extendable ment, each pair of blankets is supported by an extendable ment, each pair of blankets is supported by an extendable mast. This work was performed in Canoga Park, Calif., by mast. This work was performed in Canoga Park, Calif., by mast. This work was performed in Canoga Park, Calif., by Boeing’s former Rocketdyne division. Boeing’s former Rocketdyne division. Boeing’s former Rocketdyne division. Also in California, the Huntington Beach team made a Also in California, the Huntington Beach team made a Also in California, the Huntington Beach team made a variety of contributions to the ISS program. They devel- variety of contributions to the ISS program. They devel- variety of contributions to the ISS program. They devel- oped and built the station’s pre-integrated truss structure, oped and built the station’s pre-integrated truss structure, oped and built the station’s pre-integrated truss structure, pressurized mating adapters, and mobile transporter. They pressurized mating adapters, and mobile transporter. They pressurized mating adapters, and mobile transporter. They also led the development efforts of several subsystems, also led the development efforts of several subsystems, also led the development efforts of several subsystems, such as communications and tracking, command and such as communications and tracking, command and such as communications and tracking, command and data handling, and thermal control. data handling, and thermal control. data handling, and thermal control.

Boeing Current Operations Boeing Current Operations Boeing Current Operations

Boeing is responsible for leading efforts on the U.S. seg- Boeing is responsible for leading efforts on the U.S. seg- Boeing is responsible for leading efforts on the U.S. seg- ments of the station. These segments include the U.S. ments of the station. These segments include the U.S. ments of the station. These segments include the U.S. Destiny Laboratory, interconnecting nodes and structures, Destiny Laboratory, interconnecting nodes and structures, Destiny Laboratory, interconnecting nodes and structures, the ISS power, data management, environmental control, the ISS power, data management, environmental control, the ISS power, data management, environmental control, and life support systems, as well as other critical hardware and life support systems, as well as other critical hardware and life support systems, as well as other critical hardware

B-1 B-1 B-1 and software devices. In addition to designing and building and software devices. In addition to designing and building and software devices. In addition to designing and building all the major U.S. elements, Boeing is responsible for the all the major U.S. elements, Boeing is responsible for the all the major U.S. elements, Boeing is responsible for the successful integration of any new hardware and software, successful integration of any new hardware and software, successful integration of any new hardware and software, including that from international partners. Boeing verifica- including that from international partners. Boeing verifica- including that from international partners. Boeing verifica- tion teams effectively combine these ISS components to tion teams effectively combine these ISS components to tion teams effectively combine these ISS components to ensure the successful operation of one of the most com- ensure the successful operation of one of the most com- ensure the successful operation of one of the most com- plex scientific collaborations to date. Fulfilling its duties plex scientific collaborations to date. Fulfilling its duties plex scientific collaborations to date. Fulfilling its duties as prime contractor, Boeing also assembles and designs as prime contractor, Boeing also assembles and designs as prime contractor, Boeing also assembles and designs payload racks, cargo carriers, internal thermal controls, payload racks, cargo carriers, internal thermal controls, payload racks, cargo carriers, internal thermal controls, internal audio-video systems, a secondary power subsys- internal audio-video systems, a secondary power subsys- internal audio-video systems, a secondary power subsys- tem, as well as other essential subsystems. tem, as well as other essential subsystems. tem, as well as other essential subsystems.

The Value of ISS The Value of ISS The Value of ISS

As the world’s only orbiting research facility, the ISS pro- As the world’s only orbiting research facility, the ISS pro- As the world’s only orbiting research facility, the ISS pro- vides a unique microgravity environment that cannot be vides a unique microgravity environment that cannot be vides a unique microgravity environment that cannot be replicated in ground laboratories. From astrobiology to replicated in ground laboratories. From astrobiology to replicated in ground laboratories. From astrobiology to materials science, the research facilities aboard the station materials science, the research facilities aboard the station materials science, the research facilities aboard the station are teeming with opportunities for scientific advancement are teeming with opportunities for scientific advancement are teeming with opportunities for scientific advancement and innovation. and innovation. and innovation.

ISS Program Benefits: ISS Program Benefits: ISS Program Benefits: • The ISS is the only platform for learning how to live • The ISS is the only platform for learning how to live • The ISS is the only platform for learning how to live and work in space for extended periods of time. and work in space for extended periods of time. and work in space for extended periods of time. • Expedition crews conduct daily science experiments • Expedition crews conduct daily science experiments • Expedition crews conduct daily science experiments across a wide variety of fields, including human physi- across a wide variety of fields, including human physi- across a wide variety of fields, including human physi- ology, gravitational biology, physical sciences, and ology, gravitational biology, physical sciences, and ology, gravitational biology, physical sciences, and Earth observation. Earth observation. Earth observation. • A scientific collaboration among 15 countries, the ISS • A scientific collaboration among 15 countries, the ISS • A scientific collaboration among 15 countries, the ISS serves as a beacon of international cooperation and serves as a beacon of international cooperation and serves as a beacon of international cooperation and human accomplishment. The successful implementa- human accomplishment. The successful implementa- human accomplishment. The successful implementa- tion, assembly, and operation of the station promotes tion, assembly, and operation of the station promotes tion, assembly, and operation of the station promotes future space exploration partnerships and positive future space exploration partnerships and positive future space exploration partnerships and positive diplomatic relations. diplomatic relations. diplomatic relations. • From engineering technologies to decision-making • From engineering technologies to decision-making • From engineering technologies to decision-making processes, the ISS provides the foundation for future processes, the ISS provides the foundation for future processes, the ISS provides the foundation for future long-duration space missions. It is the bridge to the long-duration space missions. It is the bridge to the long-duration space missions. It is the bridge to the next era of manned space exploration. next era of manned space exploration. next era of manned space exploration. • The ISS program aims to inspire students of all ages • The ISS program aims to inspire students of all ages • The ISS program aims to inspire students of all ages to pursue science, technology, engineering, and to pursue science, technology, engineering, and to pursue science, technology, engineering, and mathematics (STEM disciplines). Student engage- mathematics (STEM disciplines). Student engage- mathematics (STEM disciplines). Student engage- ment includes on-orbit question-answer sessions with ment includes on-orbit question-answer sessions with ment includes on-orbit question-answer sessions with astronauts, basic science demonstrations, and the astronauts, basic science demonstrations, and the astronauts, basic science demonstrations, and the opportunity for students to fly and conduct their own opportunity for students to fly and conduct their own opportunity for students to fly and conduct their own ISS experiments. ISS experiments. ISS experiments. A New National Laboratory A New National Laboratory A New National Laboratory

With the implementation of the 2005 NASA Authorization With the implementation of the 2005 NASA Authorization With the implementation of the 2005 NASA Authorization Act, the U.S. components of the ISS have been designated Act, the U.S. components of the ISS have been designated Act, the U.S. components of the ISS have been designated a National Lab. According to the Act, this designation will a National Lab. According to the Act, this designation will a National Lab. According to the Act, this designation will “increase the utilization of the ISS by other federal entities “increase the utilization of the ISS by other federal entities “increase the utilization of the ISS by other federal entities and the private sector.” NASA will continue its research and the private sector.” NASA will continue its research and the private sector.” NASA will continue its research agenda, with the addition of new National Lab partners, agenda, with the addition of new National Lab partners, agenda, with the addition of new National Lab partners, to maximize return on one of our greatest scientific assets. to maximize return on one of our greatest scientific assets. to maximize return on one of our greatest scientific assets. As the only national laboratory of its kind, the ISS provides As the only national laboratory of its kind, the ISS provides As the only national laboratory of its kind, the ISS provides a unique research facility to accommodate the research a unique research facility to accommodate the research a unique research facility to accommodate the research needs of both NASA and upcoming National Lab users. needs of both NASA and upcoming National Lab users. needs of both NASA and upcoming National Lab users.

B-2 B-2 B-2 Research on ISS Research on ISS Research on ISS

Space investigators from industry, academia, and govern- Space investigators from industry, academia, and govern- Space investigators from industry, academia, and govern- ment can take advantage of the diverse state-of-the-art ment can take advantage of the diverse state-of-the-art ment can take advantage of the diverse state-of-the-art facilities carried aboard the orbiting complex. In addition, facilities carried aboard the orbiting complex. In addition, facilities carried aboard the orbiting complex. In addition, “remote telescience”—meaning an interactive set of data “remote telescience”—meaning an interactive set of data “remote telescience”—meaning an interactive set of data and video links—offers the ability for scientists on the and video links—offers the ability for scientists on the and video links—offers the ability for scientists on the ground to have a direct connection with their experiments ground to have a direct connection with their experiments ground to have a direct connection with their experiments on orbit. on orbit. on orbit.

A vigorous research agenda is well underway aboard the A vigorous research agenda is well underway aboard the A vigorous research agenda is well underway aboard the ISS, yielding a steady stream of findings that increase our ISS, yielding a steady stream of findings that increase our ISS, yielding a steady stream of findings that increase our understanding of both space and Earth-bound human understanding of both space and Earth-bound human understanding of both space and Earth-bound human systems. For example, studies related to bone density loss systems. For example, studies related to bone density loss systems. For example, studies related to bone density loss associated with long-duration space flight are applicable associated with long-duration space flight are applicable associated with long-duration space flight are applicable to studies of osteoporosis and aging. to studies of osteoporosis and aging. to studies of osteoporosis and aging.

Aside from NASA’s research schedule, initial National Lab Aside from NASA’s research schedule, initial National Lab Aside from NASA’s research schedule, initial National Lab users are also reaping the benefits of a microgravity re- users are also reaping the benefits of a microgravity re- users are also reaping the benefits of a microgravity re- search environment. Even in its fledging stage, the National search environment. Even in its fledging stage, the National search environment. Even in its fledging stage, the National Lab program has enabled advancements in astrobiology Lab program has enabled advancements in astrobiology Lab program has enabled advancements in astrobiology and virulence studies. Such promising results may lead to and virulence studies. Such promising results may lead to and virulence studies. Such promising results may lead to the development of vaccines for viruses like Salmonella. the development of vaccines for viruses like Salmonella. the development of vaccines for viruses like Salmonella. Scientific results from early space station research are Scientific results from early space station research are Scientific results from early space station research are being published every month as well as those of current being published every month as well as those of current being published every month as well as those of current National Lab participants. National Lab participants. National Lab participants.

New technologies needed for future exploration mis- New technologies needed for future exploration mis- New technologies needed for future exploration mis- sions—including new materials, life support systems, and sions—including new materials, life support systems, and sions—including new materials, life support systems, and environmental monitoring—are also being tested on the environmental monitoring—are also being tested on the environmental monitoring—are also being tested on the station. It is the essential building block to continue our station. It is the essential building block to continue our station. It is the essential building block to continue our space exploration agenda and enables the discovery of space exploration agenda and enables the discovery of space exploration agenda and enables the discovery of worlds beyond our own. worlds beyond our own. worlds beyond our own.

General Science Overview General Science Overview General Science Overview Although basic research has been conducted aboard the Although basic research has been conducted aboard the Although basic research has been conducted aboard the ISS since 2000, the addition of new laboratory facilities and ISS since 2000, the addition of new laboratory facilities and ISS since 2000, the addition of new laboratory facilities and a six-person crew are greatly expanding the station's sci- a six-person crew are greatly expanding the station's sci- a six-person crew are greatly expanding the station's sci- ence capacity and broadening the scope of experiments ence capacity and broadening the scope of experiments ence capacity and broadening the scope of experiments hosted by the complex. hosted by the complex. hosted by the complex. Station residents now spend an average of about 40 crew- Station residents now spend an average of about 40 crew- Station residents now spend an average of about 40 crew- hours per week on research, up from fewer than 15 hours hours per week on research, up from fewer than 15 hours hours per week on research, up from fewer than 15 hours before the expansion to a six-person crew in May 2009. before the expansion to a six-person crew in May 2009. before the expansion to a six-person crew in May 2009. The station's NASA, European, and Japanese labs are now The station's NASA, European, and Japanese labs are now The station's NASA, European, and Japanese labs are now home to 21 refrigerator-sized internal experiment racks. home to 21 refrigerator-sized internal experiment racks. home to 21 refrigerator-sized internal experiment racks. More pressurized payloads are due for delivery in 2010. More pressurized payloads are due for delivery in 2010. More pressurized payloads are due for delivery in 2010. Eighteen power and data ports for large external experi- Eighteen power and data ports for large external experi- Eighteen power and data ports for large external experi- ments have already been delivered to the complex's U.S., ments have already been delivered to the complex's U.S., ments have already been delivered to the complex's U.S., European, and Japanese segments. Ten sites are available European, and Japanese segments. Ten sites are available European, and Japanese segments. Ten sites are available on Japan's Kibo laboratory module Exposed Facility, and on Japan's Kibo laboratory module Exposed Facility, and on Japan's Kibo laboratory module Exposed Facility, and four locations each are located on the European Space four locations each are located on the European Space four locations each are located on the European Space Agency's Columbus lab and two ExPRESS logistics car- Agency's Columbus lab and two ExPRESS logistics car- Agency's Columbus lab and two ExPRESS logistics car- riers brought to the station during space shuttle mission riers brought to the station during space shuttle mission riers brought to the station during space shuttle mission STS-129. Two more ExPRESS carriers are scheduled STS-129. Two more ExPRESS carriers are scheduled STS-129. Two more ExPRESS carriers are scheduled for launch to the station in 2010, adding four additional for launch to the station in 2010, adding four additional for launch to the station in 2010, adding four additional experiment sites. experiment sites. experiment sites.

B-3 B-3 B-3 Upon completion, the ISS will provide eight research racks, Upon completion, the ISS will provide eight research racks, Upon completion, the ISS will provide eight research racks, 16 system racks, and 10 stowage racks that support NASA 16 system racks, and 10 stowage racks that support NASA 16 system racks, and 10 stowage racks that support NASA and National Lab users’ research objectives. Key station and National Lab users’ research objectives. Key station and National Lab users’ research objectives. Key station research for ongoing expeditions will be conducted in the research for ongoing expeditions will be conducted in the research for ongoing expeditions will be conducted in the following disciplines: following disciplines: following disciplines: • Human Research and Counter Measure • Human Research and Counter Measure • Human Research and Counter Measure Development Development Development Astronauts will be able to take full advantage of three Astronauts will be able to take full advantage of three Astronauts will be able to take full advantage of three Human Research Facilities (HRFs) and numerous ac- Human Research Facilities (HRFs) and numerous ac- Human Research Facilities (HRFs) and numerous ac- companying physiological modules aboard the station companying physiological modules aboard the station companying physiological modules aboard the station to gain understanding of microgravity effects on the to gain understanding of microgravity effects on the to gain understanding of microgravity effects on the human body. human body. human body. • Technology Development • Technology Development • Technology Development From Materials International Space Station Experi- From Materials International Space Station Experi- From Materials International Space Station Experi- ment (MISSE) to Vehicle Cabin Atmosphere Monitor ment (MISSE) to Vehicle Cabin Atmosphere Monitor ment (MISSE) to Vehicle Cabin Atmosphere Monitor (VCAM), researchers are currently analyzing results (VCAM), researchers are currently analyzing results (VCAM), researchers are currently analyzing results that can lead to the development of advanced alloys, that can lead to the development of advanced alloys, that can lead to the development of advanced alloys, computer networks, and monitoring systems for future computer networks, and monitoring systems for future computer networks, and monitoring systems for future exploration and ground-based innovation. exploration and ground-based innovation. exploration and ground-based innovation. • Microgravity Biological Sciences • Microgravity Biological Sciences • Microgravity Biological Sciences Cellular analysis in a microgravity environment is a Cellular analysis in a microgravity environment is a Cellular analysis in a microgravity environment is a captivating new research field made possible with captivating new research field made possible with captivating new research field made possible with the state-of-the-art ISS research facilities. The altered the state-of-the-art ISS research facilities. The altered the state-of-the-art ISS research facilities. The altered behavior of cells in space has the potential to lead to behavior of cells in space has the potential to lead to behavior of cells in space has the potential to lead to astounding medical breakthroughs on Earth. Current astounding medical breakthroughs on Earth. Current astounding medical breakthroughs on Earth. Current and future station inhabitants use station amenities and future station inhabitants use station amenities and future station inhabitants use station amenities like the Transgenic Arabidopsis Gene Expression like the Transgenic Arabidopsis Gene Expression like the Transgenic Arabidopsis Gene Expression System (TAGES), Biological Laboratory in Columbus System (TAGES), Biological Laboratory in Columbus System (TAGES), Biological Laboratory in Columbus (BioLab), and Microgravity Experiment Locker/Incu- (BioLab), and Microgravity Experiment Locker/Incu- (BioLab), and Microgravity Experiment Locker/Incu- bator (MERLIN) to investigate both plant and animal bator (MERLIN) to investigate both plant and animal bator (MERLIN) to investigate both plant and animal cells and expedite biological advancements in ground cells and expedite biological advancements in ground cells and expedite biological advancements in ground laboratories. laboratories. laboratories. • Earth Observation and Monitoring • Earth Observation and Monitoring • Earth Observation and Monitoring With equipment like Agricultural Camera (AgCam), With equipment like Agricultural Camera (AgCam), With equipment like Agricultural Camera (AgCam), astronauts can transfer automated imagery to ground astronauts can transfer automated imagery to ground astronauts can transfer automated imagery to ground researchers within two days. This provides scientists researchers within two days. This provides scientists researchers within two days. This provides scientists vegetative insight, as well as the data necessary to vegetative insight, as well as the data necessary to vegetative insight, as well as the data necessary to monitor the availability of natural resources and our monitor the availability of natural resources and our monitor the availability of natural resources and our environmental impact. The Crew Earth Observation environmental impact. The Crew Earth Observation environmental impact. The Crew Earth Observation (CEO) program allows astronauts to take photos of (CEO) program allows astronauts to take photos of (CEO) program allows astronauts to take photos of variable events to supplement ground investigations. variable events to supplement ground investigations. variable events to supplement ground investigations. Dynamic events have included fires, floods, and volca- Dynamic events have included fires, floods, and volca- Dynamic events have included fires, floods, and volca- nic eruptions. nic eruptions. nic eruptions.

B-4 B-4 B-4 Expedition 21/22 Science Overview Expedition 21/22 Science Overview Expedition 21/22 Science Overview The Expedition 21/22 mission marks the start of the The Expedition 21/22 mission marks the start of the The Expedition 21/22 mission marks the start of the transition from assembling the International Space Sta- transition from assembling the International Space Sta- transition from assembling the International Space Sta- tion to using it for continuous scientific research in the tion to using it for continuous scientific research in the tion to using it for continuous scientific research in the fall of 2010. fall of 2010. fall of 2010. Nearly 150 operating experiments in human research, Nearly 150 operating experiments in human research, Nearly 150 operating experiments in human research, biological and physical sciences, technology develop- biological and physical sciences, technology develop- biological and physical sciences, technology develop- ment, Earth observation, and educational activities will be ment, Earth observation, and educational activities will be ment, Earth observation, and educational activities will be conducted aboard the station, including several pathfinder conducted aboard the station, including several pathfinder conducted aboard the station, including several pathfinder investigations under the auspices of the station’s new role investigations under the auspices of the station’s new role investigations under the auspices of the station’s new role as a U.S. National Laboratory. All told, Expedition 21/22 as a U.S. National Laboratory. All told, Expedition 21/22 as a U.S. National Laboratory. All told, Expedition 21/22 will support 39 new scientific investigations. will support 39 new scientific investigations. will support 39 new scientific investigations. In the past, assembly and maintenance activities have In the past, assembly and maintenance activities have In the past, assembly and maintenance activities have dominated the available time for crew work. But as dominated the available time for crew work. But as dominated the available time for crew work. But as completion of the orbiting laboratory nears, additional completion of the orbiting laboratory nears, additional completion of the orbiting laboratory nears, additional facilities, and the crew members to operate them, will en- facilities, and the crew members to operate them, will en- facilities, and the crew members to operate them, will en- able a measured increase in time devoted to research as able a measured increase in time devoted to research as able a measured increase in time devoted to research as a national and multinational laboratory. a national and multinational laboratory. a national and multinational laboratory. Among the new National Laboratory Pathfinder (NLP) in- Among the new National Laboratory Pathfinder (NLP) in- Among the new National Laboratory Pathfinder (NLP) in- vestigations are the latest experiments in the NLP Vaccine vestigations are the latest experiments in the NLP Vaccine vestigations are the latest experiments in the NLP Vaccine series, which will follow up on recent discoveries about how series, which will follow up on recent discoveries about how series, which will follow up on recent discoveries about how the infectious nature of some germs can be controlled. The the infectious nature of some germs can be controlled. The the infectious nature of some germs can be controlled. The NLP Vaccine research is aimed at developing vaccines NLP Vaccine research is aimed at developing vaccines NLP Vaccine research is aimed at developing vaccines against microbial pathogens, with results already obtained against microbial pathogens, with results already obtained against microbial pathogens, with results already obtained targeting Salmonella bacteria that cause diarrhea. targeting Salmonella bacteria that cause diarrhea. targeting Salmonella bacteria that cause diarrhea. Outside the station, the new Materials International Space Outside the station, the new Materials International Space Outside the station, the new Materials International Space Station Experiment, MISSE 7, was installed by the STS-129 Station Experiment, MISSE 7, was installed by the STS-129 Station Experiment, MISSE 7, was installed by the STS-129 crew of Atlantis. MISSE 7 is testing space suit materials crew of Atlantis. MISSE 7 is testing space suit materials crew of Atlantis. MISSE 7 is testing space suit materials for use on the lunar surface and materials for the new for use on the lunar surface and materials for the new for use on the lunar surface and materials for the new solar arrays being designed for NASA’s Orion spacecraft, solar arrays being designed for NASA’s Orion spacecraft, solar arrays being designed for NASA’s Orion spacecraft, evaluating how well they withstand the effects of atomic evaluating how well they withstand the effects of atomic evaluating how well they withstand the effects of atomic oxygen, ultraviolet, direct sunlight, radiation, and extremes oxygen, ultraviolet, direct sunlight, radiation, and extremes oxygen, ultraviolet, direct sunlight, radiation, and extremes of heat and cold. of heat and cold. of heat and cold. The work of more than 400 scientists, this research has The work of more than 400 scientists, this research has The work of more than 400 scientists, this research has been prioritized based on fundamental and applied re- been prioritized based on fundamental and applied re- been prioritized based on fundamental and applied re- search needs established by NASA and the international search needs established by NASA and the international search needs established by NASA and the international partners—the Canadian Space Agency (CSA), European partners—the Canadian Space Agency (CSA), European partners—the Canadian Space Agency (CSA), European Space Agency (ESA), Japan Aerospace Exploration Agen- Space Agency (ESA), Japan Aerospace Exploration Agen- Space Agency (ESA), Japan Aerospace Exploration Agen- cy (JAXA), and Russian Federal Space Agency (RSA). cy (JAXA), and Russian Federal Space Agency (RSA). cy (JAXA), and Russian Federal Space Agency (RSA). Managing the international laboratory’s scientific assets, Managing the international laboratory’s scientific assets, Managing the international laboratory’s scientific assets, as well as the time and space required to accommodate as well as the time and space required to accommodate as well as the time and space required to accommodate experiments and programs, from a host of private, commer- experiments and programs, from a host of private, commer- experiments and programs, from a host of private, commer- cial, industry, and government agencies nationwide, makes cial, industry, and government agencies nationwide, makes cial, industry, and government agencies nationwide, makes the job of coordinating space station research critical. the job of coordinating space station research critical. the job of coordinating space station research critical. Teams of controllers and scientists on the ground continu- Teams of controllers and scientists on the ground continu- Teams of controllers and scientists on the ground continu- ously plan, monitor, and remotely operate experiments ously plan, monitor, and remotely operate experiments ously plan, monitor, and remotely operate experiments from control centers around the globe. Controllers staff from control centers around the globe. Controllers staff from control centers around the globe. Controllers staff payload operations centers all over the world, effectively payload operations centers all over the world, effectively payload operations centers all over the world, effectively providing for researchers and the station crew around the providing for researchers and the station crew around the providing for researchers and the station crew around the clock, seven days a week. clock, seven days a week. clock, seven days a week.

B-5 B-5 B-5 State-of-the-art computers and communications equip- State-of-the-art computers and communications equip- State-of-the-art computers and communications equip- ment deliver up-to-the-minute reports about experiment ment deliver up-to-the-minute reports about experiment ment deliver up-to-the-minute reports about experiment facilities and investigations between science outposts facilities and investigations between science outposts facilities and investigations between science outposts across the United States and around the world. The across the United States and around the world. The across the United States and around the world. The payload operations team also synchronizes the payload payload operations team also synchronizes the payload payload operations team also synchronizes the payload timelines among international partners, ensuring the best timelines among international partners, ensuring the best timelines among international partners, ensuring the best use of valuable resources and crew time. use of valuable resources and crew time. use of valuable resources and crew time. The control centers of NASA and its partners are: The control centers of NASA and its partners are: The control centers of NASA and its partners are: • NASA Payload Operations Center, Marshall Space • NASA Payload Operations Center, Marshall Space • NASA Payload Operations Center, Marshall Space Flight Center in Huntsville, Ala. Flight Center in Huntsville, Ala. Flight Center in Huntsville, Ala. • RSA Center for Control of Spaceflights (“TsUP” in • RSA Center for Control of Spaceflights (“TsUP” in • RSA Center for Control of Spaceflights (“TsUP” in Russian) in Korolev, Russia Russian) in Korolev, Russia Russian) in Korolev, Russia • JAXA Space Station Integration and Promotion Center • JAXA Space Station Integration and Promotion Center • JAXA Space Station Integration and Promotion Center (SSIPC) in Tskuba, Japan (SSIPC) in Tskuba, Japan (SSIPC) in Tskuba, Japan • ESA Columbus Control Center (Col-CC) in • ESA Columbus Control Center (Col-CC) in • ESA Columbus Control Center (Col-CC) in Oberpfaffenhofen, Germany Oberpfaffenhofen, Germany Oberpfaffenhofen, Germany • CSA Payloads Operations Telesciences Center, • CSA Payloads Operations Telesciences Center, • CSA Payloads Operations Telesciences Center, St. Hubert, Quebec, Canada St. Hubert, Quebec, Canada St. Hubert, Quebec, Canada NASA’s Payload Operations Center serves as a hub for co- NASA’s Payload Operations Center serves as a hub for co- NASA’s Payload Operations Center serves as a hub for co- ordinating much of the work related to delivery of research ordinating much of the work related to delivery of research ordinating much of the work related to delivery of research facilities and experiments to the space station as they facilities and experiments to the space station as they facilities and experiments to the space station as they are rotated in and out periodically when space shuttles are rotated in and out periodically when space shuttles are rotated in and out periodically when space shuttles or other vehicles make deliveries and return completed or other vehicles make deliveries and return completed or other vehicles make deliveries and return completed experiments and samples to Earth. experiments and samples to Earth. experiments and samples to Earth.

The payload operations director leads the POC’s main The payload operations director leads the POC’s main The payload operations director leads the POC’s main flight control team, known as the "cadre," and approves flight control team, known as the "cadre," and approves flight control team, known as the "cadre," and approves all science plans in coordination with Mission Control at all science plans in coordination with Mission Control at all science plans in coordination with Mission Control at NASA's Johnson Space Center in Houston, the interna- NASA's Johnson Space Center in Houston, the interna- NASA's Johnson Space Center in Houston, the interna- tional partner control centers, and the station crew. tional partner control centers, and the station crew. tional partner control centers, and the station crew.

Expedition 21/22 continues the tradition of scientific Expedition 21/22 continues the tradition of scientific Expedition 21/22 continues the tradition of scientific activities aboard the ISS that began with Expedition 1 in activities aboard the ISS that began with Expedition 1 in activities aboard the ISS that began with Expedition 1 in 2000. Myriad activities include experiments that require 2000. Myriad activities include experiments that require 2000. Myriad activities include experiments that require crew support, as well as automated experiments that are crew support, as well as automated experiments that are crew support, as well as automated experiments that are ongoing without crew efforts. ongoing without crew efforts. ongoing without crew efforts.

U.S. experiments include: U.S. experiments include: U.S. experiments include:

Amateur Radio on the International Space Station (ARISS) Amateur Radio on the International Space Station (ARISS) Amateur Radio on the International Space Station (ARISS) allows crew aboard the ISS, with the help of Amateur Radio allows crew aboard the ISS, with the help of Amateur Radio allows crew aboard the ISS, with the help of Amateur Radio Clubs and ham radio operators, to speak directly with Clubs and ham radio operators, to speak directly with Clubs and ham radio operators, to speak directly with groups of the general public, showing teachers, students, groups of the general public, showing teachers, students, groups of the general public, showing teachers, students, parents, and communities how amateur radio can motivate parents, and communities how amateur radio can motivate parents, and communities how amateur radio can motivate students’ learning about science and technology. students’ learning about science and technology. students’ learning about science and technology.

Crew Earth Observations (CEO) takes advantage of hav- Crew Earth Observations (CEO) takes advantage of hav- Crew Earth Observations (CEO) takes advantage of hav- ing the crew in space to observe and photograph natural ing the crew in space to observe and photograph natural ing the crew in space to observe and photograph natural and human-made changes on Earth. The photographs and human-made changes on Earth. The photographs and human-made changes on Earth. The photographs record the Earth’s surface changes over time, along with record the Earth’s surface changes over time, along with record the Earth’s surface changes over time, along with dynamic events such as storms, floods, fires, and volcanic dynamic events such as storms, floods, fires, and volcanic dynamic events such as storms, floods, fires, and volcanic eruptions. These images provide researchers on Earth with eruptions. These images provide researchers on Earth with eruptions. These images provide researchers on Earth with key data to better understand the planet. key data to better understand the planet. key data to better understand the planet.

B-6 B-6 B-6 Psychomotor Vigilance Self-Test consists of a 5-minute Psychomotor Vigilance Self-Test consists of a 5-minute Psychomotor Vigilance Self-Test consists of a 5-minute reaction time task that allows crew members to monitor reaction time task that allows crew members to monitor reaction time task that allows crew members to monitor the daily effects of fatigue on performance while on the the daily effects of fatigue on performance while on the the daily effects of fatigue on performance while on the ISS. The experiment provides objective feedback on neu- ISS. The experiment provides objective feedback on neu- ISS. The experiment provides objective feedback on neu- robehavioral changes in attention, psychomotor speed, robehavioral changes in attention, psychomotor speed, robehavioral changes in attention, psychomotor speed, state stability, and impulsivity while on ISS missions, state stability, and impulsivity while on ISS missions, state stability, and impulsivity while on ISS missions, particularly as they relate to changes in circadian rhythms, particularly as they relate to changes in circadian rhythms, particularly as they relate to changes in circadian rhythms, sleep restrictions, and extended work shifts. sleep restrictions, and extended work shifts. sleep restrictions, and extended work shifts. The Nutritional Status Assessment is the most compre- The Nutritional Status Assessment is the most compre- The Nutritional Status Assessment is the most compre- hensive in-flight study done by NASA to date of human hensive in-flight study done by NASA to date of human hensive in-flight study done by NASA to date of human physiologic changes during long-duration space flight. It physiologic changes during long-duration space flight. It physiologic changes during long-duration space flight. It includes measures of bone metabolism, oxidative dam- includes measures of bone metabolism, oxidative dam- includes measures of bone metabolism, oxidative dam- age, nutritional assessments, and hormonal changes. age, nutritional assessments, and hormonal changes. age, nutritional assessments, and hormonal changes. This study will impact both the definition of nutritional This study will impact both the definition of nutritional This study will impact both the definition of nutritional requirements and development of food systems for future requirements and development of food systems for future requirements and development of food systems for future space exploration missions to the moon and Mars. This space exploration missions to the moon and Mars. This space exploration missions to the moon and Mars. This experiment will also help to understand the impact of coun- experiment will also help to understand the impact of coun- experiment will also help to understand the impact of coun- termeasures (exercise and pharmaceuticals) on nutritional termeasures (exercise and pharmaceuticals) on nutritional termeasures (exercise and pharmaceuticals) on nutritional status and nutrient requirements for astronauts. status and nutrient requirements for astronauts. status and nutrient requirements for astronauts. The Biological Specimen Repository is a storage bank that The Biological Specimen Repository is a storage bank that The Biological Specimen Repository is a storage bank that is used to maintain biological specimens over extended is used to maintain biological specimens over extended is used to maintain biological specimens over extended periods of time and under well-controlled conditions. periods of time and under well-controlled conditions. periods of time and under well-controlled conditions. Biological samples from the ISS, including blood and Biological samples from the ISS, including blood and Biological samples from the ISS, including blood and urine, are collected, processed, and archived during urine, are collected, processed, and archived during urine, are collected, processed, and archived during the preflight, in-flight, and postflight phases of ISS mis- the preflight, in-flight, and postflight phases of ISS mis- the preflight, in-flight, and postflight phases of ISS mis- sions. This investigation has been developed to archive sions. This investigation has been developed to archive sions. This investigation has been developed to archive biosamples for use as a resource for future space flight- biosamples for use as a resource for future space flight- biosamples for use as a resource for future space flight- related research. related research. related research.

Sleep-Wake Actigraphy and Light Exposure During Sleep-Wake Actigraphy and Light Exposure During Sleep-Wake Actigraphy and Light Exposure During Space Flight–Long examines the effects of space flight Space Flight–Long examines the effects of space flight Space Flight–Long examines the effects of space flight and ambient light exposure on the sleep-wake cycles and ambient light exposure on the sleep-wake cycles and ambient light exposure on the sleep-wake cycles of the crew members during long-duration stays on the of the crew members during long-duration stays on the of the crew members during long-duration stays on the space station. space station. space station.

Automated U.S. experiments (ongoing without crew ef- Automated U.S. experiments (ongoing without crew ef- Automated U.S. experiments (ongoing without crew ef- forts) include: forts) include: forts) include: HREP—the Hyperspectral Imager for the Coastal Ocean HREP—the Hyperspectral Imager for the Coastal Ocean HREP—the Hyperspectral Imager for the Coastal Ocean (HICO) and Remote Atmospheric and Ionospheric Detec- (HICO) and Remote Atmospheric and Ionospheric Detec- (HICO) and Remote Atmospheric and Ionospheric Detec- tion System (RAIDS) Experiment Payload—operates a tion System (RAIDS) Experiment Payload—operates a tion System (RAIDS) Experiment Payload—operates a visible and near-infrared (VNIR) maritime hyperspectral visible and near-infrared (VNIR) maritime hyperspectral visible and near-infrared (VNIR) maritime hyperspectral imaging (MHSI) system to detect, identify, and quantify imaging (MHSI) system to detect, identify, and quantify imaging (MHSI) system to detect, identify, and quantify coastal geophysical features from the ISS. The experiment coastal geophysical features from the ISS. The experiment coastal geophysical features from the ISS. The experiment provides atmospheric scientists with a complete descrip- provides atmospheric scientists with a complete descrip- provides atmospheric scientists with a complete descrip- tion of the major constituents of the thermosphere (layer of tion of the major constituents of the thermosphere (layer of tion of the major constituents of the thermosphere (layer of the Earth’s atmosphere) and ionosphere (uppermost layer the Earth’s atmosphere) and ionosphere (uppermost layer the Earth’s atmosphere) and ionosphere (uppermost layer of the Earth’s atmosphere) global electron density profiles of the Earth’s atmosphere) global electron density profiles of the Earth’s atmosphere) global electron density profiles at altitudes between 100 to 350 kilometers. at altitudes between 100 to 350 kilometers. at altitudes between 100 to 350 kilometers. Microgravity Acceleration Measurement System (MAMS) Microgravity Acceleration Measurement System (MAMS) Microgravity Acceleration Measurement System (MAMS) and Space Acceleration Measurement System-II (SAMS-II) and Space Acceleration Measurement System-II (SAMS-II) and Space Acceleration Measurement System-II (SAMS-II) measure the ISS vibrational accelerations during specific measure the ISS vibrational accelerations during specific measure the ISS vibrational accelerations during specific periods of operations. MAMS and SAMS-II further the periods of operations. MAMS and SAMS-II further the periods of operations. MAMS and SAMS-II further the understanding of accelerations resulting from physical understanding of accelerations resulting from physical understanding of accelerations resulting from physical disturbances on the ISS. MAMS and SAMS-II also help char- disturbances on the ISS. MAMS and SAMS-II also help char- disturbances on the ISS. MAMS and SAMS-II also help char- acterize accelerations that may affect ISS experiments. acterize accelerations that may affect ISS experiments. acterize accelerations that may affect ISS experiments.

B-7 B-7 B-7 International partner experiments include: International partner experiments include: International partner experiments include:

BioRhythms examines the effect of long-term micrograv- BioRhythms examines the effect of long-term micrograv- BioRhythms examines the effect of long-term micrograv- ity exposure on cardiac autonomic function by analyzing ity exposure on cardiac autonomic function by analyzing ity exposure on cardiac autonomic function by analyzing 24-hour electrocardiograms. 24-hour electrocardiograms. 24-hour electrocardiograms.

Bodies in the Space Environment: (BISE) evaluates ad- Bodies in the Space Environment: (BISE) evaluates ad- Bodies in the Space Environment: (BISE) evaluates ad- aptation to, the effect of, and recovery from long-duration aptation to, the effect of, and recovery from long-duration aptation to, the effect of, and recovery from long-duration microgravity exposure on the self-perception of orientation microgravity exposure on the self-perception of orientation microgravity exposure on the self-perception of orientation using the Oriented Character Recognition Test (OCHART) using the Oriented Character Recognition Test (OCHART) using the Oriented Character Recognition Test (OCHART) protocol. protocol. protocol.

Japan Aerospace Exploration Agency–Education Payload Japan Aerospace Exploration Agency–Education Payload Japan Aerospace Exploration Agency–Education Payload Observation (JAXA–EPO) aims to generate interest in Observation (JAXA–EPO) aims to generate interest in Observation (JAXA–EPO) aims to generate interest in microgravity research and human space flight. Activities microgravity research and human space flight. Activities microgravity research and human space flight. Activities include educational events and artistic activities with include educational events and artistic activities with include educational events and artistic activities with astronauts on orbit. astronauts on orbit. astronauts on orbit.

Matroshka has been an ongoing experiment on the ISS Matroshka has been an ongoing experiment on the ISS Matroshka has been an ongoing experiment on the ISS since February 2004, with the aim of studying radiation since February 2004, with the aim of studying radiation since February 2004, with the aim of studying radiation levels experienced by astronauts. It consists of a man- levels experienced by astronauts. It consists of a man- levels experienced by astronauts. It consists of a man- nequin (head and torso) called the Phantom equipped nequin (head and torso) called the Phantom equipped nequin (head and torso) called the Phantom equipped with several active and passive radiation dosimeters to with several active and passive radiation dosimeters to with several active and passive radiation dosimeters to study cosmic radiation dose types and rates that space study cosmic radiation dose types and rates that space study cosmic radiation dose types and rates that space travelers would experience on long-duration missions. The travelers would experience on long-duration missions. The travelers would experience on long-duration missions. The experiment is named for the Matryoshka dolls, or Russian experiment is named for the Matryoshka dolls, or Russian experiment is named for the Matryoshka dolls, or Russian nested dolls, that have various layers of dolls, with the inner nested dolls, that have various layers of dolls, with the inner nested dolls, that have various layers of dolls, with the inner layers revealed when the outer layers are opened. In this layers revealed when the outer layers are opened. In this layers revealed when the outer layers are opened. In this experiment, the doll has measured the radiation doses of experiment, the doll has measured the radiation doses of experiment, the doll has measured the radiation doses of the separate components of the ionizing cosmic radia- the separate components of the ionizing cosmic radia- the separate components of the ionizing cosmic radia- tion at the skin surface and at different locations inside tion at the skin surface and at different locations inside tion at the skin surface and at different locations inside a realistic human torso, in order to establish the relation a realistic human torso, in order to establish the relation a realistic human torso, in order to establish the relation between skin doses and organ doses. Matroshka also acts between skin doses and organ doses. Matroshka also acts between skin doses and organ doses. Matroshka also acts as a simulation of a spacesuit worn by astronauts during as a simulation of a spacesuit worn by astronauts during as a simulation of a spacesuit worn by astronauts during a spacewalk. The torso uses commercial parts, common a spacewalk. The torso uses commercial parts, common a spacewalk. The torso uses commercial parts, common to the field of radiotherapy; various instrumented “slices” to the field of radiotherapy; various instrumented “slices” to the field of radiotherapy; various instrumented “slices” were composed of natural bones embedded in plastics, were composed of natural bones embedded in plastics, were composed of natural bones embedded in plastics, simulating tissue and lungs. simulating tissue and lungs. simulating tissue and lungs.

Mice Drawer System (MDS) is an experiment that uses Mice Drawer System (MDS) is an experiment that uses Mice Drawer System (MDS) is an experiment that uses a validated mouse model to investigate the genetic a validated mouse model to investigate the genetic a validated mouse model to investigate the genetic mechanisms underlying bone mass loss in microgravity. mechanisms underlying bone mass loss in microgravity. mechanisms underlying bone mass loss in microgravity. Research conducted with the MDS is an analog to the hu- Research conducted with the MDS is an analog to the hu- Research conducted with the MDS is an analog to the hu- man research program, which has the objective to extend man research program, which has the objective to extend man research program, which has the objective to extend the human presence safely beyond low Earth orbit. the human presence safely beyond low Earth orbit. the human presence safely beyond low Earth orbit.

SOdium LOading in Microgravity (SOLO) is a continuation SOdium LOading in Microgravity (SOLO) is a continuation SOdium LOading in Microgravity (SOLO) is a continuation of extensive research into the mechanisms of fluid and salt of extensive research into the mechanisms of fluid and salt of extensive research into the mechanisms of fluid and salt retention in the body during bed rest and space flights. retention in the body during bed rest and space flights. retention in the body during bed rest and space flights. Astronauts participate in two metabolically controlled Astronauts participate in two metabolically controlled Astronauts participate in two metabolically controlled study phases of 5 days each. Subjects follow a diet of study phases of 5 days each. Subjects follow a diet of study phases of 5 days each. Subjects follow a diet of constant either low or normal sodium intake, fairly high constant either low or normal sodium intake, fairly high constant either low or normal sodium intake, fairly high fluid consumption, and isocaloric nutrition. fluid consumption, and isocaloric nutrition. fluid consumption, and isocaloric nutrition.

SpaceSeed is undertaken to cultivate Arabidopsis thali- SpaceSeed is undertaken to cultivate Arabidopsis thali- SpaceSeed is undertaken to cultivate Arabidopsis thali- ana, which has a relatively short life cycle in microgravity. ana, which has a relatively short life cycle in microgravity. ana, which has a relatively short life cycle in microgravity. The controlling mechanism of developmental processes The controlling mechanism of developmental processes The controlling mechanism of developmental processes in Arabidopsis has been physiologically and genetically in Arabidopsis has been physiologically and genetically in Arabidopsis has been physiologically and genetically - B-8 B-8 B-8 studied with various mutants and transgenic plants studied with various mutants and transgenic plants studied with various mutants and transgenic plants on Earth. The experiments with Arabidopsis under the on Earth. The experiments with Arabidopsis under the on Earth. The experiments with Arabidopsis under the microgravity environment on ISS will provide important microgravity environment on ISS will provide important microgravity environment on ISS will provide important information for improving the productivity of crops in space information for improving the productivity of crops in space information for improving the productivity of crops in space as well as for understanding the role of gravity in regulating as well as for understanding the role of gravity in regulating as well as for understanding the role of gravity in regulating the life cycle of higher plants. the life cycle of higher plants. the life cycle of higher plants.

Yeast-B examines the effect of microgravity on specific Yeast-B examines the effect of microgravity on specific Yeast-B examines the effect of microgravity on specific proteins of yeast cells (Saccharomyces cerevisiae). This proteins of yeast cells (Saccharomyces cerevisiae). This proteins of yeast cells (Saccharomyces cerevisiae). This two-part investigation uses two different types of cul- two-part investigation uses two different types of cul- two-part investigation uses two different types of cul- tures—liquid and solid. The objective of the investigation is tures—liquid and solid. The objective of the investigation is tures—liquid and solid. The objective of the investigation is to provide scientists with data on the impact of microgravity to provide scientists with data on the impact of microgravity to provide scientists with data on the impact of microgravity on organized cell structures. on organized cell structures. on organized cell structures.

Automated international partner experiments (ongoing Automated international partner experiments (ongoing Automated international partner experiments (ongoing without crew efforts) include: without crew efforts) include: without crew efforts) include:

Monitor of All-sky X-ray Image (MAXI) is an externally Monitor of All-sky X-ray Image (MAXI) is an externally Monitor of All-sky X-ray Image (MAXI) is an externally mounted experiment to be attached on the Japanese mounted experiment to be attached on the Japanese mounted experiment to be attached on the Japanese Experiment Module (JEM) Exposed Facility. MAXI consists Experiment Module (JEM) Exposed Facility. MAXI consists Experiment Module (JEM) Exposed Facility. MAXI consists of highly sensitive X-ray slit cameras for the monitoring of of highly sensitive X-ray slit cameras for the monitoring of of highly sensitive X-ray slit cameras for the monitoring of more than 1,000 X-ray sources in space over an energy more than 1,000 X-ray sources in space over an energy more than 1,000 X-ray sources in space over an energy band range of 0.5 to 30 keV band range of 0.5 to 30 keV band range of 0.5 to 30 keV

Passive Dosimeter for Lifescience Experiment in Space Passive Dosimeter for Lifescience Experiment in Space Passive Dosimeter for Lifescience Experiment in Space (PADLES) uses passive and integrating dosimeters to (PADLES) uses passive and integrating dosimeters to (PADLES) uses passive and integrating dosimeters to detect radiation levels on board the ISS. These dosimeters detect radiation levels on board the ISS. These dosimeters detect radiation levels on board the ISS. These dosimeters are located near the biological experiment facilities and on are located near the biological experiment facilities and on are located near the biological experiment facilities and on the end of the JEM. The dosimeters measure absorbed the end of the JEM. The dosimeters measure absorbed the end of the JEM. The dosimeters measure absorbed doses, equivalent doses, and liner energy transfer (LET) doses, equivalent doses, and liner energy transfer (LET) doses, equivalent doses, and liner energy transfer (LET) distributions. distributions. distributions.

Space Environment Data Acquisition Equipment–Attached Space Environment Data Acquisition Equipment–Attached Space Environment Data Acquisition Equipment–Attached Payload (SEDA-AP) measures the space environment Payload (SEDA-AP) measures the space environment Payload (SEDA-AP) measures the space environment (neutrons, plasma, heavy ions, high-energy light par- (neutrons, plasma, heavy ions, high-energy light par- (neutrons, plasma, heavy ions, high-energy light par- ticles, atomic oxygen, and cosmic dust) in ISS orbit and ticles, atomic oxygen, and cosmic dust) in ISS orbit and ticles, atomic oxygen, and cosmic dust) in ISS orbit and environmental effects on materials and electronic devices environmental effects on materials and electronic devices environmental effects on materials and electronic devices to investigate the interaction with and from the space to investigate the interaction with and from the space to investigate the interaction with and from the space environment at the JEM EF. At the same time, it conducts environment at the JEM EF. At the same time, it conducts environment at the JEM EF. At the same time, it conducts on-orbit verification of Attached Payload Bus (APBUS) on-orbit verification of Attached Payload Bus (APBUS) on-orbit verification of Attached Payload Bus (APBUS) technology, which furnishes necessary functions when technology, which furnishes necessary functions when technology, which furnishes necessary functions when mounted on the JEM EF. mounted on the JEM EF. mounted on the JEM EF.

Superconduction Submillimeter-wave Limb-emission Superconduction Submillimeter-wave Limb-emission Superconduction Submillimeter-wave Limb-emission Sounder (SMILES) is aimed at global mappings of Sounder (SMILES) is aimed at global mappings of Sounder (SMILES) is aimed at global mappings of stratospheric trace gases by means of the most sensitive stratospheric trace gases by means of the most sensitive stratospheric trace gases by means of the most sensitive submillimeter receiver. Such sensitivity is ascribed to a submillimeter receiver. Such sensitivity is ascribed to a submillimeter receiver. Such sensitivity is ascribed to a superconductor-insulator-superconductor (SIS) mixer, superconductor-insulator-superconductor (SIS) mixer, superconductor-insulator-superconductor (SIS) mixer, which is operated at 4.5 K in a dedicated cryostat com- which is operated at 4.5 K in a dedicated cryostat com- which is operated at 4.5 K in a dedicated cryostat com- bined with a mechanical cooler. bined with a mechanical cooler. bined with a mechanical cooler.

Sun Monitoring on the External Payload Facility of Co- Sun Monitoring on the External Payload Facility of Co- Sun Monitoring on the External Payload Facility of Co- lumbus (Solar) is a monitoring observatory that measures lumbus (Solar) is a monitoring observatory that measures lumbus (Solar) is a monitoring observatory that measures solar spectral irradiance. Apart from scientific contribu- solar spectral irradiance. Apart from scientific contribu- solar spectral irradiance. Apart from scientific contribu- tions for solar and stellar physics, the knowledge of the tions for solar and stellar physics, the knowledge of the tions for solar and stellar physics, the knowledge of the solar energy irradiance into the Earth’s atmosphere and solar energy irradiance into the Earth’s atmosphere and solar energy irradiance into the Earth’s atmosphere and

B-9 B-9 B-9 its variations is of great importance for atmospheric its variations is of great importance for atmospheric its variations is of great importance for atmospheric modeling, atmospheric chemistry, and climatology. Solar modeling, atmospheric chemistry, and climatology. Solar modeling, atmospheric chemistry, and climatology. Solar consists of three instruments complementing each other consists of three instruments complementing each other consists of three instruments complementing each other to allow measurements of the solar spectral irradiance to allow measurements of the solar spectral irradiance to allow measurements of the solar spectral irradiance throughout virtually the whole electromagnetic spectrum, throughout virtually the whole electromagnetic spectrum, throughout virtually the whole electromagnetic spectrum, from 17 nanometers to 100 micrometers, in which 99% of from 17 nanometers to 100 micrometers, in which 99% of from 17 nanometers to 100 micrometers, in which 99% of the solar energy is emitted. The scientific instruments are the solar energy is emitted. The scientific instruments are the solar energy is emitted. The scientific instruments are SOlar Variable and Irradiance Monitor (SOVIM), which SOlar Variable and Irradiance Monitor (SOVIM), which SOlar Variable and Irradiance Monitor (SOVIM), which covers near-ultraviolet, visible, and thermal regions of the covers near-ultraviolet, visible, and thermal regions of the covers near-ultraviolet, visible, and thermal regions of the spectrum (200 nanometers to 100 micrometers); SOLar spectrum (200 nanometers to 100 micrometers); SOLar spectrum (200 nanometers to 100 micrometers); SOLar SPECtral Irradiance Measurements (SOLSPEC), which SPECtral Irradiance Measurements (SOLSPEC), which SPECtral Irradiance Measurements (SOLSPEC), which covers the 180-nanometer to 3,000-nanometer range covers the 180-nanometer to 3,000-nanometer range covers the 180-nanometer to 3,000-nanometer range with high spectral resolution; and SOLar Auto-Calibrating with high spectral resolution; and SOLar Auto-Calibrating with high spectral resolution; and SOLar Auto-Calibrating Extreme UV/UV Spectrometers (SOLACES), which mea- Extreme UV/UV Spectrometers (SOLACES), which mea- Extreme UV/UV Spectrometers (SOLACES), which mea- sures the EUV/UV spectral regime (17 nanometers to 220 sures the EUV/UV spectral regime (17 nanometers to 220 sures the EUV/UV spectral regime (17 nanometers to 220 nanometers) with moderate spectral resolution. nanometers) with moderate spectral resolution. nanometers) with moderate spectral resolution.

On the Internet: For fact sheets, imagery, and more on On the Internet: For fact sheets, imagery, and more on On the Internet: For fact sheets, imagery, and more on Expedition 21/22 experiments and payload operations, Expedition 21/22 experiments and payload operations, Expedition 21/22 experiments and payload operations, visit: visit: visit:

http://www.nasa.gov/mission_pages/station/science/ http://www.nasa.gov/mission_pages/station/science/ http://www.nasa.gov/mission_pages/station/science/ index.htm index.htm index.htm

For general information about science on the ISS, visit: For general information about science on the ISS, visit: For general information about science on the ISS, visit:

http://www.nasa.gov/mission_pages/station/science/ http://www.nasa.gov/mission_pages/station/science/ http://www.nasa.gov/mission_pages/station/science/ index.htm index.htm index.htm

B-10 B-10 B-10 ISS FACTS ISS FACTS ISS FACTS (weights approximate) (weights approximate) (weights approximate)

Measurements (at completion) Measurements (at completion) Measurements (at completion) Solar Array Wingspan: 356 ft (108.5 m) Solar Array Wingspan: 356 ft (108.5 m) Solar Array Wingspan: 356 ft (108.5 m) (port to starboard) (port to starboard) (port to starboard) Length: 170.6 ft (52.0 m) Length: 170.6 ft (52.0 m) Length: 170.6 ft (52.0 m) (pressurized section) (pressurized section) (pressurized section) Integrated Truss Length: 323.25 ft (98.6 m) Integrated Truss Length: 323.25 ft (98.6 m) Integrated Truss Length: 323.25 ft (98.6 m) Mass (weight): 925,627 lb Mass (weight): 925,627 lb Mass (weight): 925,627 lb (419,857 kg) (419,857 kg) (419,857 kg) Operating Altitude: 220 nmi average Operating Altitude: 220 nmi average Operating Altitude: 220 nmi average (407 km) (407 km) (407 km) Inclination: 51.6 deg to the equator Inclination: 51.6 deg to the equator Inclination: 51.6 deg to the equator Atmosphere Inside: 14.7 psi Atmosphere Inside: 14.7 psi Atmosphere Inside: 14.7 psi (101.36 kilopascals), (101.36 kilopascals), (101.36 kilopascals), same as Earth same as Earth same as Earth Pressurized Volume: 34,700 ft3 (983 m3) Pressurized Volume: 34,700 ft3 (983 m3) Pressurized Volume: 34,700 ft3 (983 m3) (assumes a Soyuz and (assumes a Soyuz and (assumes a Soyuz and Progress vehicle are Progress vehicle are Progress vehicle are docked to station) docked to station) docked to station) Crew Size: Six Crew Size: Six Crew Size: Six Speed: 17,500 mph Speed: 17,500 mph Speed: 17,500 mph Robotic Arms: 55-ft robot arm assembly Robotic Arms: 55-ft robot arm assembly Robotic Arms: 55-ft robot arm assembly that can lift 220,000 lb and that can lift 220,000 lb and that can lift 220,000 lb and is used for assembly of is used for assembly of is used for assembly of main ISS; 30-ft robotic main ISS; 30-ft robotic main ISS; 30-ft robotic arm based on Kibo and arm based on Kibo and arm based on Kibo and used to move and deploy used to move and deploy used to move and deploy experiments on the experiments on the experiments on the Japanese External Facility Japanese External Facility Japanese External Facility Power Generation: 84-120 kilowatts (usable) Power Generation: 84-120 kilowatts (usable) Power Generation: 84-120 kilowatts (usable)

The Partners The Partners The Partners

The ISS is a partnership among five space agencies from The ISS is a partnership among five space agencies from The ISS is a partnership among five space agencies from the United States, Canada, multiple European states, the United States, Canada, multiple European states, the United States, Canada, multiple European states, Japan, and Russia. Japan, and Russia. Japan, and Russia.

B-11 B-11 B-11 ISS Confi guration as of Mission STS-129/ISS-ULF3 ISS Confi guration as of Mission STS-129/ISS-ULF3 ISS Confi guration as of Mission STS-129/ISS-ULF3 (November 2009) (November 2009) (November 2009)

Final ISS Confi guration Final ISS Confi guration Final ISS Confi guration

B-12 B-12 B-12 ISS Element Statistics (as of January 2010) ISS Element Statistics (as of January 2010) ISS Element Statistics (as of January 2010) Weight Weight Weight Weight Weight Weight Module (lb) (kg) Launched Module (lb) (kg) Launched Module (lb) (kg) Launched

Zarya 50,419 22,870 11/20/98 Zarya 50,419 22,870 11/20/98 Zarya 50,419 22,870 11/20/98 Node 1 "Unity" 24,711 11,209 12/04/98 Node 1 "Unity" 24,711 11,209 12/04/98 Node 1 "Unity" 24,711 11,209 12/04/98 PMA-1 3,504 1,589 12/04/98 PMA-1 3,504 1,589 12/04/98 PMA-1 3,504 1,589 12/04/98 PMA-2 3,033 1,376 12/04/98 PMA-2 3,033 1,376 12/04/98 PMA-2 3,033 1,376 12/04/98 Zvezda 53,267 24,162 07/12/00 Zvezda 53,267 24,162 07/12/00 Zvezda 53,267 24,162 07/12/00 Z1 Truss 19,227 8,721 10/11/00 Z1 Truss 19,227 8,721 10/11/00 Z1 Truss 19,227 8,721 10/11/00 PMA-3 2,575 1,168 10/11/00 PMA-3 2,575 1,168 10/11/00 PMA-3 2,575 1,168 10/11/00 Soyuz 15,762 7,150 Soyuz 15,762 7,150 Soyuz 15,762 7,150 P6 Truss 30,689 13,920 11/30/00 P6 Truss 30,689 13,920 11/30/00 P6 Truss 30,689 13,920 11/30/00 U.S. Lab "Destiny" 53,602 24,313 02/07/01 U.S. Lab "Destiny" 53,602 24,313 02/07/01 U.S. Lab "Destiny" 53,602 24,313 02/07/01 External Stowage 145 66 03/08/01 External Stowage 145 66 03/08/01 External Stowage 145 66 03/08/01 Platform 1 Platform 1 Platform 1 Canadarm2 3,311 1,502 04/19/01 Canadarm2 3,311 1,502 04/19/01 Canadarm2 3,311 1,502 04/19/01 Joint Airlock "Quest" 20,831 9,449 07/12/01 Joint Airlock "Quest" 20,831 9,449 07/12/01 Joint Airlock "Quest" 20,831 9,449 07/12/01 Progress 15,200 6,895 Progress 15,200 6,895 Progress 15,200 6,895 Pirs 7,150 3,243 09/15/01 Pirs 7,150 3,243 09/15/01 Pirs 7,150 3,243 09/15/01 S0 Truss 24,890 11,290 04/08/02 S0 Truss 24,890 11,290 04/08/02 S0 Truss 24,890 11,290 04/08/02 Mobile Base System 3,000 1,361 06/05/02 Mobile Base System 3,000 1,361 06/05/02 Mobile Base System 3,000 1,361 06/05/02 S1 Truss 31,137 14,124 10/07/02 S1 Truss 31,137 14,124 10/07/02 S1 Truss 31,137 14,124 10/07/02 CETA-A 540 245 10/07/02 CETA-A 540 245 10/07/02 CETA-A 540 245 10/07/02 P1 Truss 30,871 14,003 11/23/02 P1 Truss 30,871 14,003 11/23/02 P1 Truss 30,871 14,003 11/23/02 CETA-B 540 245 11/23/02 CETA-B 540 245 11/23/02 CETA-B 540 245 11/23/02 External Stowage 5,900 2,676 07/26/05 External Stowage 5,900 2,676 07/26/05 External Stowage 5,900 2,676 07/26/05 Platform 2 Platform 2 Platform 2 P3/P4 Truss 34,700 15,740 09/09/06 P3/P4 Truss 34,700 15,740 09/09/06 P3/P4 Truss 34,700 15,740 09/09/06 P5 Truss 4,107 1,863 12/09/06 P5 Truss 4,107 1,863 12/09/06 P5 Truss 4,107 1,863 12/09/06 S3/S4 Truss 35,678 16,183 06/08/07 S3/S4 Truss 35,678 16,183 06/08/07 S3/S4 Truss 35,678 16,183 06/08/07 S5 Truss 4,040 1,833 08/08/07 S5 Truss 4,040 1,833 08/08/07 S5 Truss 4,040 1,833 08/08/07 External Stowage 6,937 2,902 08/08/07 External Stowage 6,937 2,902 08/08/07 External Stowage 6,937 2,902 08/08/07 Platform 3 Platform 3 Platform 3 Node 2 "Harmony" 31,500 14,300 10/23/07 Node 2 "Harmony" 31,500 14,300 10/23/07 Node 2 "Harmony" 31,500 14,300 10/23/07 Columbus Science 29,458 13,362 02/11/08 Columbus Science 29,458 13,362 02/11/08 Columbus Science 29,458 13,362 02/11/08 Laboratory Laboratory Laboratory Kibo ELM-PS 18,490 8,387 03/11/08 Kibo ELM-PS 18,490 8,387 03/11/08 Kibo ELM-PS 18,490 8,387 03/11/08 Kibo JEM-PM 32,628 14,800 05/31/08 Kibo JEM-PM 32,628 14,800 05/31/08 Kibo JEM-PM 32,628 14,800 05/31/08 S6 Truss 30,937 14,033 03/15/09 S6 Truss 30,937 14,033 03/15/09 S6 Truss 30,937 14,033 03/15/09 Kibo EF 8,200 3,719 07/15/09 Kibo EF 8,200 3,719 07/15/09 Kibo EF 8,200 3,719 07/15/09 Kibo ELM-ES 2,400 1,089 07/15/09 Kibo ELM-ES 2,400 1,089 07/15/09 Kibo ELM-ES 2,400 1,089 07/15/09 Mini-Research Module 2 8,201 3,720 11/10/09 Mini-Research Module 2 8,201 3,720 11/10/09 Mini-Research Module 2 8,201 3,720 11/10/09 ExPRESS Logistics 9,800 4,445 11/16/09 ExPRESS Logistics 9,800 4,445 11/16/09 ExPRESS Logistics 9,800 4,445 11/16/09 Carriers (2) Carriers (2) Carriers (2) Current Total: 171 ft long (pressurized); 323.25 ft Current Total: 171 ft long (pressurized); 323.25 ft Current Total: 171 ft long (pressurized); 323.25 ft wide (solar arrays); 48.9 ft high wide (solar arrays); 48.9 ft high wide (solar arrays); 48.9 ft high (fixed structure); 759,222 lb; ISS is (fixed structure); 759,222 lb; ISS is (fixed structure); 759,222 lb; ISS is 86% complete 86% complete 86% complete ISS Elements to Be Added ISS Elements to Be Added ISS Elements to Be Added Node 3 "Tranquility" 33,551 lb (15,218 kg) Node 3 "Tranquility" 33,551 lb (15,218 kg) Node 3 "Tranquility" 33,551 lb (15,218 kg) Cupola 3,732 lb (1,693 kg) Cupola 3,732 lb (1,693 kg) Cupola 3,732 lb (1,693 kg) Mini-Research Module 1 10,362 lb (4,700 kg) Mini-Research Module 1 10,362 lb (4,700 kg) Mini-Research Module 1 10,362 lb (4,700 kg) Alpha Magnetic Spectrometer 14,809 lb (6,717 kg) Alpha Magnetic Spectrometer 14,809 lb (6,717 kg) Alpha Magnetic Spectrometer 14,809 lb (6,717 kg) Multipurpose Laboratory Module 44,754 lb (20,300 kg) Multipurpose Laboratory Module 44,754 lb (20,300 kg) Multipurpose Laboratory Module 44,754 lb (20,300 kg)

B-13 B-13 B-13 ISS Elements on Orbit ISS Elements on Orbit ISS Elements on Orbit

Zarya Module Zarya Module Zarya Module

The Zarya module—also known by the technical term The Zarya module—also known by the technical term The Zarya module—also known by the technical term Functional Cargo Block and the Russian acronym FGB— Functional Cargo Block and the Russian acronym FGB— Functional Cargo Block and the Russian acronym FGB— was the first component launched for the International was the first component launched for the International was the first component launched for the International Space Station. The U.S.-funded and Russian-built Zarya, Space Station. The U.S.-funded and Russian-built Zarya, Space Station. The U.S.-funded and Russian-built Zarya, which means “sunrise” when translated into English, is a which means “sunrise” when translated into English, is a which means “sunrise” when translated into English, is a U.S. component of the station, although it was built and U.S. component of the station, although it was built and U.S. component of the station, although it was built and launched by Russia. The module was built by the Khru- launched by Russia. The module was built by the Khru- launched by Russia. The module was built by the Khru- nichev State Research and Production Space Center, nichev State Research and Production Space Center, nichev State Research and Production Space Center, which is also known as KhSC, in Moscow under a sub- which is also known as KhSC, in Moscow under a sub- which is also known as KhSC, in Moscow under a sub- contract to The Boeing Company for NASA. contract to The Boeing Company for NASA. contract to The Boeing Company for NASA.

After launch, a set of preprogrammed commands auto- After launch, a set of preprogrammed commands auto- After launch, a set of preprogrammed commands auto- matically activated the module’s systems and deployed the matically activated the module’s systems and deployed the matically activated the module’s systems and deployed the solar arrays and communications antennas. Only weeks solar arrays and communications antennas. Only weeks solar arrays and communications antennas. Only weeks after Zarya reached orbit, space shuttle Endeavour made after Zarya reached orbit, space shuttle Endeavour made after Zarya reached orbit, space shuttle Endeavour made a rendezvous and attached a U.S.-built connecting mod- a rendezvous and attached a U.S.-built connecting mod- a rendezvous and attached a U.S.-built connecting mod- ule called Node 1, or Unity. The subsequently launched ule called Node 1, or Unity. The subsequently launched ule called Node 1, or Unity. The subsequently launched Zvezda service module, a Russian-provided crew living Zvezda service module, a Russian-provided crew living Zvezda service module, a Russian-provided crew living quarters and early station core, enhanced or replaced quarters and early station core, enhanced or replaced quarters and early station core, enhanced or replaced many functions of Zarya. The Zarya module is now used many functions of Zarya. The Zarya module is now used many functions of Zarya. The Zarya module is now used primarily for its storage capacity and external fuel tanks. primarily for its storage capacity and external fuel tanks. primarily for its storage capacity and external fuel tanks.

Launched atop a Russian Proton rocket from the Baikonur Launched atop a Russian Proton rocket from the Baikonur Launched atop a Russian Proton rocket from the Baikonur Cosmodrome, Kazakhstan, launch site, Zarya provides Cosmodrome, Kazakhstan, launch site, Zarya provides Cosmodrome, Kazakhstan, launch site, Zarya provides battery power, fuel storage, and rendezvous and docking battery power, fuel storage, and rendezvous and docking battery power, fuel storage, and rendezvous and docking capability for Soyuz and Progress space vehicles. capability for Soyuz and Progress space vehicles. capability for Soyuz and Progress space vehicles.

Zarya’s side docking ports accommodate Russian Soyuz Zarya’s side docking ports accommodate Russian Soyuz Zarya’s side docking ports accommodate Russian Soyuz piloted spacecraft and unpiloted Progress resupply piloted spacecraft and unpiloted Progress resupply piloted spacecraft and unpiloted Progress resupply spacecraft. The module’s 16 fuel tanks combined can spacecraft. The module’s 16 fuel tanks combined can spacecraft. The module’s 16 fuel tanks combined can hold more than 6 tons (5.4 metric tons) of propellant. The hold more than 6 tons (5.4 metric tons) of propellant. The hold more than 6 tons (5.4 metric tons) of propellant. The

B-14 B-14 B-14 attitude control system for the module includes 24 large attitude control system for the module includes 24 large attitude control system for the module includes 24 large steering jets and 12 small steering jets. Two large engines steering jets and 12 small steering jets. Two large engines steering jets and 12 small steering jets. Two large engines were available for reboosting the spacecraft and making were available for reboosting the spacecraft and making were available for reboosting the spacecraft and making major orbital changes before Zvezda arrived. major orbital changes before Zvezda arrived. major orbital changes before Zvezda arrived. Length: 41.2 ft (12.6 m) Length: 41.2 ft (12.6 m) Length: 41.2 ft (12.6 m) Width: 13.5 ft (4.1 m) Width: 13.5 ft (4.1 m) Width: 13.5 ft (4.1 m) Weight: 50,419 lb (22,870 kg) Weight: 50,419 lb (22,870 kg) Weight: 50,419 lb (22,870 kg)

Node 1 "Unity" Node 1 "Unity" Node 1 "Unity"

Node 1, the first U.S.-built component of the ISS, is a Node 1, the first U.S.-built component of the ISS, is a Node 1, the first U.S.-built component of the ISS, is a cylinder-shaped connecting module with six passage- cylinder-shaped connecting module with six passage- cylinder-shaped connecting module with six passage- ways, or nodes, to which modules were attached as the ways, or nodes, to which modules were attached as the ways, or nodes, to which modules were attached as the station expanded. station expanded. station expanded.

ISS Node 1, “Unity” module, and two pressurized mating ISS Node 1, “Unity” module, and two pressurized mating ISS Node 1, “Unity” module, and two pressurized mating adapters (PMAs) during space shuttle mission STS-88/ adapters (PMAs) during space shuttle mission STS-88/ adapters (PMAs) during space shuttle mission STS-88/ ISS-2A ISS-2A ISS-2A

Length: 18 ft (5.49 m) Length: 18 ft (5.49 m) Length: 18 ft (5.49 m) Width: 15 ft (4.57 m) Width: 15 ft (4.57 m) Width: 15 ft (4.57 m) Weight: 24,711 lb (11,209 kg) Weight: 24,711 lb (11,209 kg) Weight: 24,711 lb (11,209 kg)

Zvezda Service Module Zvezda Service Module Zvezda Service Module

The service module was the first fully Russian contribution The service module was the first fully Russian contribution The service module was the first fully Russian contribution to the ISS and served as the early cornerstone for the first to the ISS and served as the early cornerstone for the first to the ISS and served as the early cornerstone for the first human habitation of the station. human habitation of the station. human habitation of the station.

The module provided the early station living quarters, The module provided the early station living quarters, The module provided the early station living quarters, life support system, electrical power distribution, data life support system, electrical power distribution, data life support system, electrical power distribution, data processing system, flight control system, and propulsion processing system, flight control system, and propulsion processing system, flight control system, and propulsion system. It also provided a communications system that system. It also provided a communications system that system. It also provided a communications system that included remote command capabilities from ground included remote command capabilities from ground included remote command capabilities from ground flight controllers. Although many of these systems were flight controllers. Although many of these systems were flight controllers. Although many of these systems were supplemented or replaced by U.S. station components, supplemented or replaced by U.S. station components, supplemented or replaced by U.S. station components, the service module will always remain the structural and the service module will always remain the structural and the service module will always remain the structural and functional center of the Russian segment of the ISS. functional center of the Russian segment of the ISS. functional center of the Russian segment of the ISS. Length: 43 ft (13.1 m) Length: 43 ft (13.1 m) Length: 43 ft (13.1 m) Width (wingspan): 97.5 ft (29.7 m) Width (wingspan): 97.5 ft (29.7 m) Width (wingspan): 97.5 ft (29.7 m) Weight: 53,267 lb (24,162 kg) Weight: 53,267 lb (24,162 kg) Weight: 53,267 lb (24,162 kg)

B-15 B-15 B-15 Launched atop a Russian Proton rocket from Baikonur Launched atop a Russian Proton rocket from Baikonur Launched atop a Russian Proton rocket from Baikonur Cosmodrome, Zvezda joined the ISS, docked with Zarya Cosmodrome, Zvezda joined the ISS, docked with Zarya Cosmodrome, Zvezda joined the ISS, docked with Zarya and a Progress supply vehicle. and a Progress supply vehicle. and a Progress supply vehicle.

Node 2 "Harmony" Node 2 "Harmony" Node 2 "Harmony"

Harmony, also known as Node 2, was the first pressur- Harmony, also known as Node 2, was the first pressur- Harmony, also known as Node 2, was the first pressur- ized module added to the station since the Russian Pirs ized module added to the station since the Russian Pirs ized module added to the station since the Russian Pirs Docking Compartment was installed in September 2001. Docking Compartment was installed in September 2001. Docking Compartment was installed in September 2001. Harmony is a utility hub, providing air, electrical power, Harmony is a utility hub, providing air, electrical power, Harmony is a utility hub, providing air, electrical power, water, and other systems essential to support life on the water, and other systems essential to support life on the water, and other systems essential to support life on the station. It distributes resources from the station’s truss to station. It distributes resources from the station’s truss to station. It distributes resources from the station’s truss to the Destiny lab and to the European Space Agency’s Co- the Destiny lab and to the European Space Agency’s Co- the Destiny lab and to the European Space Agency’s Co- lumbus Science Laboratory and the Japanese Experiment lumbus Science Laboratory and the Japanese Experiment lumbus Science Laboratory and the Japanese Experiment Module (Kibo). The module acts as an internal connecting Module (Kibo). The module acts as an internal connecting Module (Kibo). The module acts as an internal connecting port and passageway to additional international science port and passageway to additional international science port and passageway to additional international science labs and cargo spacecraft. labs and cargo spacecraft. labs and cargo spacecraft.

In addition to increasing the living and working space in- In addition to increasing the living and working space in- In addition to increasing the living and working space in- side the station by more than 2,500 cubic feet, its exterior side the station by more than 2,500 cubic feet, its exterior side the station by more than 2,500 cubic feet, its exterior serves as a work platform for the station’s robotic arm, serves as a work platform for the station’s robotic arm, serves as a work platform for the station’s robotic arm, Canadarm2. Harmony is similar in shape to the six-sided Canadarm2. Harmony is similar in shape to the six-sided Canadarm2. Harmony is similar in shape to the six-sided Unity module, known also as Node 1. Unity links the Des- Unity module, known also as Node 1. Unity links the Des- Unity module, known also as Node 1. Unity links the Des- tiny lab and the Russian Zarya Module. tiny lab and the Russian Zarya Module. tiny lab and the Russian Zarya Module. Length: 23.6 ft (7.2 m) Length: 23.6 ft (7.2 m) Length: 23.6 ft (7.2 m) Width: 14.5 ft (4.4 m) Width: 14.5 ft (4.4 m) Width: 14.5 ft (4.4 m) Weight: 31,500 lb (14,300 kg) Weight: 31,500 lb (14,300 kg) Weight: 31,500 lb (14,300 kg) Node 2 received its name after an academic competition Node 2 received its name after an academic competition Node 2 received its name after an academic competition involving students from 32 states. Six different schools involving students from 32 states. Six different schools involving students from 32 states. Six different schools submitted “Harmony.” A panel of NASA educators, engi- submitted “Harmony.” A panel of NASA educators, engi- submitted “Harmony.” A panel of NASA educators, engi- neers, scientists, and senior agency managers selected neers, scientists, and senior agency managers selected neers, scientists, and senior agency managers selected the name because it symbolizes the spirit of international the name because it symbolizes the spirit of international the name because it symbolizes the spirit of international cooperation embodied by the station, as well as the mod- cooperation embodied by the station, as well as the mod- cooperation embodied by the station, as well as the mod- ule’s specific role in connecting the international partner ule’s specific role in connecting the international partner ule’s specific role in connecting the international partner modules. modules. modules.

Harmony was designed and built for NASA by Thales Harmony was designed and built for NASA by Thales Harmony was designed and built for NASA by Thales Alenia Space in Torino, Italy, as part of an agreement Alenia Space in Torino, Italy, as part of an agreement Alenia Space in Torino, Italy, as part of an agreement between NASA and the ESA. The Boeing Company between NASA and the ESA. The Boeing Company between NASA and the ESA. The Boeing Company

B-16 B-16 B-16 provided a large number of Harmony’s subsystem provided a large number of Harmony’s subsystem provided a large number of Harmony’s subsystem components, including lights, fans, power switches and components, including lights, fans, power switches and components, including lights, fans, power switches and converters, racks, air diffusers, smoke detectors, hatches, converters, racks, air diffusers, smoke detectors, hatches, converters, racks, air diffusers, smoke detectors, hatches, and passive common berthing mechanisms. and passive common berthing mechanisms. and passive common berthing mechanisms.

Boeing also built, installed onto Harmony, and tested Boeing also built, installed onto Harmony, and tested Boeing also built, installed onto Harmony, and tested five active common berthing mechanisms (ACBMs). The five active common berthing mechanisms (ACBMs). The five active common berthing mechanisms (ACBMs). The mechanisms enable on-orbit mating and airtight seals mechanisms enable on-orbit mating and airtight seals mechanisms enable on-orbit mating and airtight seals between ISS pressurized elements. The ACBMs consist between ISS pressurized elements. The ACBMs consist between ISS pressurized elements. The ACBMs consist of powered, computer-controlled components that align of powered, computer-controlled components that align of powered, computer-controlled components that align capture and are secured to passive CBMs. capture and are secured to passive CBMs. capture and are secured to passive CBMs.

While the ACBM contains all of the powered components While the ACBM contains all of the powered components While the ACBM contains all of the powered components and associated alignment hardware for berthing, the pas- and associated alignment hardware for berthing, the pas- and associated alignment hardware for berthing, the pas- sive CBM configurations include the reciprocal mating fit- sive CBM configurations include the reciprocal mating fit- sive CBM configurations include the reciprocal mating fit- tings and alignment components. In a precisely controlled tings and alignment components. In a precisely controlled tings and alignment components. In a precisely controlled sequence of events, the ISS remote manipulation system sequence of events, the ISS remote manipulation system sequence of events, the ISS remote manipulation system positions the mating module passive CBM near the ISS positions the mating module passive CBM near the ISS positions the mating module passive CBM near the ISS ACBM for automated berthing, resulting in a structurally ACBM for automated berthing, resulting in a structurally ACBM for automated berthing, resulting in a structurally sealed assembly. sealed assembly. sealed assembly.

Harmony’s installation was a two-step process. First, Harmony’s installation was a two-step process. First, Harmony’s installation was a two-step process. First, STS-120/Discovery docked to pressurized mating adapter STS-120/Discovery docked to pressurized mating adapter STS-120/Discovery docked to pressurized mating adapter 2 (PMA-2), located on the end of Destiny. Then the crew 2 (PMA-2), located on the end of Destiny. Then the crew 2 (PMA-2), located on the end of Destiny. Then the crew attached the new module to a temporary position on the attached the new module to a temporary position on the attached the new module to a temporary position on the outside of Unity. outside of Unity. outside of Unity.

In the grasp of the station’s Canadarm2, Harmony is In the grasp of the station’s Canadarm2, Harmony is In the grasp of the station’s Canadarm2, Harmony is moved from its stowage position in the cargo bay of space moved from its stowage position in the cargo bay of space moved from its stowage position in the cargo bay of space shuttle Discovery to its temporary location on the ISS. shuttle Discovery to its temporary location on the ISS. shuttle Discovery to its temporary location on the ISS.

After Discovery left, the Expedition 16 crew used Cana- After Discovery left, the Expedition 16 crew used Cana- After Discovery left, the Expedition 16 crew used Cana- darm2 to move PMA-2 to the forward port, onto one of the darm2 to move PMA-2 to the forward port, onto one of the darm2 to move PMA-2 to the forward port, onto one of the five ACBMs on Harmony. Then, the crew used the arm to five ACBMs on Harmony. Then, the crew used the arm to five ACBMs on Harmony. Then, the crew used the arm to move and install Harmony at its permanent location at move and install Harmony at its permanent location at move and install Harmony at its permanent location at the end of Destiny. the end of Destiny. the end of Destiny.

B-17 B-17 B-17 U.S. Laboratory “Destiny” U.S. Laboratory “Destiny” U.S. Laboratory “Destiny” Length: 28 ft (8.5 m) Length: 28 ft (8.5 m) Length: 28 ft (8.5 m) Width: 14 ft (4.3 m) Width: 14 ft (4.3 m) Width: 14 ft (4.3 m) Weight: 53,602 lb (24,313 kg) Weight: 53,602 lb (24,313 kg) Weight: 53,602 lb (24,313 kg) Volume: 3,750 ft3 (106 m3) Volume: 3,750 ft3 (106 m3) Volume: 3,750 ft3 (106 m3) Windows: 1 - 20 in. (50.9 cm) Windows: 1 - 20 in. (50.9 cm) Windows: 1 - 20 in. (50.9 cm) No. of Racks: 24 (13 scientific and No. of Racks: 24 (13 scientific and No. of Racks: 24 (13 scientific and 11 system) 11 system) 11 system) Exterior: Aluminum “waffle” pattern, Exterior: Aluminum “waffle” pattern, Exterior: Aluminum “waffle” pattern, covered with an insulation covered with an insulation covered with an insulation blanket and intermediate blanket and intermediate blanket and intermediate debris shield debris shield debris shield

The Destiny Laboratory after its delivery and installation The Destiny Laboratory after its delivery and installation The Destiny Laboratory after its delivery and installation by the STS-98/ISS-5A crew, as seen from the departing by the STS-98/ISS-5A crew, as seen from the departing by the STS-98/ISS-5A crew, as seen from the departing space shuttle Atlantis space shuttle Atlantis space shuttle Atlantis

Considered the centerpiece of the International Space Considered the centerpiece of the International Space Considered the centerpiece of the International Space Station, “Destiny,” the U.S. Laboratory module, is a world- Station, “Destiny,” the U.S. Laboratory module, is a world- Station, “Destiny,” the U.S. Laboratory module, is a world- class, state-of-the-art research facility in a microgravity class, state-of-the-art research facility in a microgravity class, state-of-the-art research facility in a microgravity environment. Destiny provides astronauts a year-round, environment. Destiny provides astronauts a year-round, environment. Destiny provides astronauts a year-round, shirt sleeve atmosphere for research in many areas, shirt sleeve atmosphere for research in many areas, shirt sleeve atmosphere for research in many areas, including life science, microgravity science, Earth sci- including life science, microgravity science, Earth sci- including life science, microgravity science, Earth sci- ence, and space science research. The facilities inside ence, and space science research. The facilities inside ence, and space science research. The facilities inside the lab are designed to yield a steady stream of findings the lab are designed to yield a steady stream of findings the lab are designed to yield a steady stream of findings from hundreds of high-quality science and technology from hundreds of high-quality science and technology from hundreds of high-quality science and technology experiments. It is the primary workstation for the U.S. experiments. It is the primary workstation for the U.S. experiments. It is the primary workstation for the U.S. involvement on the ISS. involvement on the ISS. involvement on the ISS.

B-18 B-18 B-18 Destiny comprises three cylindrical sections and two end- Destiny comprises three cylindrical sections and two end- Destiny comprises three cylindrical sections and two end- cones. Each end-cone contains a hatch opening through cones. Each end-cone contains a hatch opening through cones. Each end-cone contains a hatch opening through which the astronauts enter and exit the lab. which the astronauts enter and exit the lab. which the astronauts enter and exit the lab.

Made of aluminum, the exterior of the laboratory module Made of aluminum, the exterior of the laboratory module Made of aluminum, the exterior of the laboratory module has a "waffle" pattern that strengthens the hull. It is covered has a "waffle" pattern that strengthens the hull. It is covered has a "waffle" pattern that strengthens the hull. It is covered with an insulation blanket to protect the module from the with an insulation blanket to protect the module from the with an insulation blanket to protect the module from the harsh temperatures of outer space. harsh temperatures of outer space. harsh temperatures of outer space.

An intermediate debris shield made of material similar to An intermediate debris shield made of material similar to An intermediate debris shield made of material similar to that of bulletproof vests protects the module against space that of bulletproof vests protects the module against space that of bulletproof vests protects the module against space debris and micrometeoroids. debris and micrometeoroids. debris and micrometeoroids.

An aluminum debris shield was placed over the intermedi- An aluminum debris shield was placed over the intermedi- An aluminum debris shield was placed over the intermedi- ate debris shield for added protection and to reflect the ate debris shield for added protection and to reflect the ate debris shield for added protection and to reflect the intense sunlight to reduce the load on the air conditioning intense sunlight to reduce the load on the air conditioning intense sunlight to reduce the load on the air conditioning system. system. system.

Inside, four "stand-off" structures provide space for power Inside, four "stand-off" structures provide space for power Inside, four "stand-off" structures provide space for power lines, data management systems, vacuum systems, air lines, data management systems, vacuum systems, air lines, data management systems, vacuum systems, air conditioning ducts, water lines, and more, all supporting conditioning ducts, water lines, and more, all supporting conditioning ducts, water lines, and more, all supporting the space station's racks. the space station's racks. the space station's racks.

There are 24 racks inside the laboratory, six on each There are 24 racks inside the laboratory, six on each There are 24 racks inside the laboratory, six on each side. Thirteen are scientific racks dedicated to various side. Thirteen are scientific racks dedicated to various side. Thirteen are scientific racks dedicated to various science experiments, and 11 racks provide power, cool- science experiments, and 11 racks provide power, cool- science experiments, and 11 racks provide power, cool- ing water, temperature and humidity control, as well as ing water, temperature and humidity control, as well as ing water, temperature and humidity control, as well as air revitalization to remove carbon dioxide and replenish air revitalization to remove carbon dioxide and replenish air revitalization to remove carbon dioxide and replenish oxygen. Destiny has a 20-inch (50.9-centimeter) optically oxygen. Destiny has a 20-inch (50.9-centimeter) optically oxygen. Destiny has a 20-inch (50.9-centimeter) optically pure, telescope-quality glass window located in an open pure, telescope-quality glass window located in an open pure, telescope-quality glass window located in an open rack bay used primarily for Earth science observations. rack bay used primarily for Earth science observations. rack bay used primarily for Earth science observations. Station crew members use very high-quality video and Station crew members use very high-quality video and Station crew members use very high-quality video and still cameras at the window to record Earth's changing still cameras at the window to record Earth's changing still cameras at the window to record Earth's changing landscapes. A window shutter protects the window from landscapes. A window shutter protects the window from landscapes. A window shutter protects the window from potential micrometeoroid and orbital debris strikes during potential micrometeoroid and orbital debris strikes during potential micrometeoroid and orbital debris strikes during the life of the ISS. The crew manually opens the shutter the life of the ISS. The crew manually opens the shutter the life of the ISS. The crew manually opens the shutter to use the window. to use the window. to use the window.

Each rack is 73-inches (1.9-meters) tall and 42-inches Each rack is 73-inches (1.9-meters) tall and 42-inches Each rack is 73-inches (1.9-meters) tall and 42-inches (1.1-meters) wide, basically the size of the average (1.1-meters) wide, basically the size of the average (1.1-meters) wide, basically the size of the average household closet. Made with a graphite composite shell, household closet. Made with a graphite composite shell, household closet. Made with a graphite composite shell, racks inside the ISS lab weigh around 1,200 pounds (544 racks inside the ISS lab weigh around 1,200 pounds (544 racks inside the ISS lab weigh around 1,200 pounds (544 kilograms) each. kilograms) each. kilograms) each.

Boeing began construction of the 16-ton (14.5-tonne) Boeing began construction of the 16-ton (14.5-tonne) Boeing began construction of the 16-ton (14.5-tonne) state-of-the-art research laboratory in 1995 at Marshall state-of-the-art research laboratory in 1995 at Marshall state-of-the-art research laboratory in 1995 at Marshall Space Flight Center in Huntsville, Alabama. Destiny was Space Flight Center in Huntsville, Alabama. Destiny was Space Flight Center in Huntsville, Alabama. Destiny was shipped to Kennedy Space Center in Florida in 1998 and shipped to Kennedy Space Center in Florida in 1998 and shipped to Kennedy Space Center in Florida in 1998 and was turned over to NASA for prelaunch preparations in was turned over to NASA for prelaunch preparations in was turned over to NASA for prelaunch preparations in August 2000. It launched on Feb. 7, 2001, aboard the August 2000. It launched on Feb. 7, 2001, aboard the August 2000. It launched on Feb. 7, 2001, aboard the space shuttle Atlantis on STS-98. space shuttle Atlantis on STS-98. space shuttle Atlantis on STS-98.

B-19 B-19 B-19 U.S. Laboratory “Destiny” Confi guration U.S. Laboratory “Destiny” Confi guration U.S. Laboratory “Destiny” Confi guration

28 ft 28 ft 28 ft

14 ft 14 ft 14 ft

Materials Sciences Materials Sciences Materials Sciences Standard Rack-1 Standard Rack-1 Standard Rack-1 (example) (example) (example) Rack Facts Rack Facts Rack Facts Height: 73 in. (1.9 m) Height: 73 in. (1.9 m) Height: 73 in. (1.9 m) Width: 42 in. (1.1 m) Width: 42 in. (1.1 m) Width: 42 in. (1.1 m) Weight: 1,200 lb (544 kg) Weight: 1,200 lb (544 kg) Weight: 1,200 lb (544 kg) Exterior: Graphite composite shell Exterior: Graphite composite shell Exterior: Graphite composite shell

Columbus Laboratory Columbus Laboratory Columbus Laboratory

The Columbus Laboratory is the cornerstone of the Euro- The Columbus Laboratory is the cornerstone of the Euro- The Columbus Laboratory is the cornerstone of the Euro- pean Space Agency’s contribution to the ISS and is the pean Space Agency’s contribution to the ISS and is the pean Space Agency’s contribution to the ISS and is the first European laboratory dedicated to long-term research first European laboratory dedicated to long-term research first European laboratory dedicated to long-term research in space. Named after the famous explorer from Genoa, in space. Named after the famous explorer from Genoa, in space. Named after the famous explorer from Genoa, the Columbus Laboratory gives an enormous boost to cur- the Columbus Laboratory gives an enormous boost to cur- the Columbus Laboratory gives an enormous boost to cur- rent European experiment facilities in weightlessness and rent European experiment facilities in weightlessness and rent European experiment facilities in weightlessness and to the research capabilities of the ISS. It has internal and to the research capabilities of the ISS. It has internal and to the research capabilities of the ISS. It has internal and external accommodations for numerous experiments in life external accommodations for numerous experiments in life external accommodations for numerous experiments in life sciences, fluid physics, and a host of other disciplines. sciences, fluid physics, and a host of other disciplines. sciences, fluid physics, and a host of other disciplines.

The Columbus Laboratory is photographed by an STS-122 The Columbus Laboratory is photographed by an STS-122 The Columbus Laboratory is photographed by an STS-122 crew member on space shuttle Atlantis shortly after the crew member on space shuttle Atlantis shortly after the crew member on space shuttle Atlantis shortly after the undocking of the two spacecraft. undocking of the two spacecraft. undocking of the two spacecraft.

B-20 B-20 B-20 The Columbus Laboratory consists of a pressurized The Columbus Laboratory consists of a pressurized The Columbus Laboratory consists of a pressurized cylindrical hull closed with welded end cones. To reduce cylindrical hull closed with welded end cones. To reduce cylindrical hull closed with welded end cones. To reduce costs and maintain high reliability, the laboratory shares costs and maintain high reliability, the laboratory shares costs and maintain high reliability, the laboratory shares its basic structure and life support systems with the its basic structure and life support systems with the its basic structure and life support systems with the European-built MPLMs. European-built MPLMs. European-built MPLMs.

The primary and internal secondary structures of Colum- The primary and internal secondary structures of Colum- The primary and internal secondary structures of Colum- bus are constructed from aluminum alloys. These layers bus are constructed from aluminum alloys. These layers bus are constructed from aluminum alloys. These layers are covered with a multilayer insulation blanket for thermal are covered with a multilayer insulation blanket for thermal are covered with a multilayer insulation blanket for thermal stability and a further two tons of paneling constructed stability and a further two tons of paneling constructed stability and a further two tons of paneling constructed of an aluminium alloy together with a layer of Kevlar and of an aluminium alloy together with a layer of Kevlar and of an aluminium alloy together with a layer of Kevlar and Nextel to act as protection from space debris. Nextel to act as protection from space debris. Nextel to act as protection from space debris.

The Columbus Laboratory has an internal volume of 2,646 The Columbus Laboratory has an internal volume of 2,646 The Columbus Laboratory has an internal volume of 2,646 cubic feet (75 cubic meters), which can accommodate 16 cubic feet (75 cubic meters), which can accommodate 16 cubic feet (75 cubic meters), which can accommodate 16 racks arranged around the circumference of the cylindri- racks arranged around the circumference of the cylindri- racks arranged around the circumference of the cylindri- cal section in four sets of four racks. These racks have cal section in four sets of four racks. These racks have cal section in four sets of four racks. These racks have standard dimensions with standard interfaces, used in all standard dimensions with standard interfaces, used in all standard dimensions with standard interfaces, used in all non-Russian modules, and can hold experimental facilities non-Russian modules, and can hold experimental facilities non-Russian modules, and can hold experimental facilities or subsystems. or subsystems. or subsystems. Length: 23 ft (7 m) Length: 23 ft (7 m) Length: 23 ft (7 m) Width: 15 ft (4.5 m) Width: 15 ft (4.5 m) Width: 15 ft (4.5 m) Weight: 29,458 lb (13,362 kg) Weight: 29,458 lb (13,362 kg) Weight: 29,458 lb (13,362 kg) Ten of the 16 are International Standard Payload Racks Ten of the 16 are International Standard Payload Racks Ten of the 16 are International Standard Payload Racks (ISPRs) fully outfitted with resources (such as power, cool- (ISPRs) fully outfitted with resources (such as power, cool- (ISPRs) fully outfitted with resources (such as power, cool- ing, and video and data lines) to be able to accommodate ing, and video and data lines) to be able to accommodate ing, and video and data lines) to be able to accommodate an experiment facility with a mass of up to 1,543 lb (700 an experiment facility with a mass of up to 1,543 lb (700 an experiment facility with a mass of up to 1,543 lb (700 kg). The extensive experiment capability of the Columbus kg). The extensive experiment capability of the Columbus kg). The extensive experiment capability of the Columbus Laboratory has been achieved through careful optimiza- Laboratory has been achieved through careful optimiza- Laboratory has been achieved through careful optimiza- tion of the system configuration, making use of the end tion of the system configuration, making use of the end tion of the system configuration, making use of the end cones for housing subsystem equipment. The central area cones for housing subsystem equipment. The central area cones for housing subsystem equipment. The central area of the starboard cone carries system equipment such as of the starboard cone carries system equipment such as of the starboard cone carries system equipment such as video monitors and cameras, switching panels, audio video monitors and cameras, switching panels, audio video monitors and cameras, switching panels, audio terminals, and fire extinguishers. terminals, and fire extinguishers. terminals, and fire extinguishers.

Although it is the station’s smallest laboratory module, the Although it is the station’s smallest laboratory module, the Although it is the station’s smallest laboratory module, the Columbus Laboratory offers the same payload volume, Columbus Laboratory offers the same payload volume, Columbus Laboratory offers the same payload volume, power, and data retrieval as the station’s other laboratories. power, and data retrieval as the station’s other laboratories. power, and data retrieval as the station’s other laboratories. A significant benefit of this cost-saving design is that Co- A significant benefit of this cost-saving design is that Co- A significant benefit of this cost-saving design is that Co- lumbus was launched already outfitted with 5,511 lb (2,500 lumbus was launched already outfitted with 5,511 lb (2,500 lumbus was launched already outfitted with 5,511 lb (2,500 kg) of experiment facilities and additional hardware. kg) of experiment facilities and additional hardware. kg) of experiment facilities and additional hardware.

B-21 B-21 B-21 Japanese Experiment Module (Kibo) Japanese Experiment Module (Kibo) Japanese Experiment Module (Kibo) The first component of the Japanese Experiment Module The first component of the Japanese Experiment Module The first component of the Japanese Experiment Module (JEM), or Kibo, flew to the ISS after 23 years of develop- (JEM), or Kibo, flew to the ISS after 23 years of develop- (JEM), or Kibo, flew to the ISS after 23 years of develop- ment efforts by the Japan Aerospace Exploration Agency ment efforts by the Japan Aerospace Exploration Agency ment efforts by the Japan Aerospace Exploration Agency (JAXA). The Kibo facilities are used to perform collabora- (JAXA). The Kibo facilities are used to perform collabora- (JAXA). The Kibo facilities are used to perform collabora- tive experiments by all the station partners. tive experiments by all the station partners. tive experiments by all the station partners. Kibo means “hope” and is Japan’s first human-rated Kibo means “hope” and is Japan’s first human-rated Kibo means “hope” and is Japan’s first human-rated space facility. Kibo is the largest experiment module on space facility. Kibo is the largest experiment module on space facility. Kibo is the largest experiment module on the space station, accommodating 31 racks in its pressur- the space station, accommodating 31 racks in its pressur- the space station, accommodating 31 racks in its pressur- ized section, including experiment, stowage, and system ized section, including experiment, stowage, and system ized section, including experiment, stowage, and system racks. Kibo is also equipped with external facilities that can racks. Kibo is also equipped with external facilities that can racks. Kibo is also equipped with external facilities that can accommodate 10 exposed experiment payloads. accommodate 10 exposed experiment payloads. accommodate 10 exposed experiment payloads. Kibo is a complex facility that enables several kinds of Kibo is a complex facility that enables several kinds of Kibo is a complex facility that enables several kinds of specialized functions. In total, Kibo consists of six com- specialized functions. In total, Kibo consists of six com- specialized functions. In total, Kibo consists of six com- ponents: two research facilities—the Pressurized Module ponents: two research facilities—the Pressurized Module ponents: two research facilities—the Pressurized Module (PM) and Exposed Facility (EF), a Logistics Module at- (PM) and Exposed Facility (EF), a Logistics Module at- (PM) and Exposed Facility (EF), a Logistics Module at- tached to each of them, a Remote Manipulator System— tached to each of them, a Remote Manipulator System— tached to each of them, a Remote Manipulator System— the Japanese Experiment Module Remote Manipulator the Japanese Experiment Module Remote Manipulator the Japanese Experiment Module Remote Manipulator System (JEMRMS), and an Inter-Orbit Communication System (JEMRMS), and an Inter-Orbit Communication System (JEMRMS), and an Inter-Orbit Communication System. Kibo also has a scientific airlock through which System. Kibo also has a scientific airlock through which System. Kibo also has a scientific airlock through which experiments can be transferred and exposed to the ex- experiments can be transferred and exposed to the ex- experiments can be transferred and exposed to the ex- ternal environment of space. ternal environment of space. ternal environment of space.

The Kibo elements were delivered to the space station The Kibo elements were delivered to the space station The Kibo elements were delivered to the space station over the course of three space shuttle missions. STS-123 over the course of three space shuttle missions. STS-123 over the course of three space shuttle missions. STS-123 delivered the Experiment Logistics Module–Pressurized delivered the Experiment Logistics Module–Pressurized delivered the Experiment Logistics Module–Pressurized Section (ELM-PS), STS-124 delivered the PM and JEM- Section (ELM-PS), STS-124 delivered the PM and JEM- Section (ELM-PS), STS-124 delivered the PM and JEM- RMS, and STS-127 delivered the EF and the Experiment RMS, and STS-127 delivered the EF and the Experiment RMS, and STS-127 delivered the EF and the Experiment Logistics Module–Exposed Section (ELM-ES). For each Logistics Module–Exposed Section (ELM-ES). For each Logistics Module–Exposed Section (ELM-ES). For each of the missions, a JAXA astronaut flew to the station to of the missions, a JAXA astronaut flew to the station to of the missions, a JAXA astronaut flew to the station to assist with the assembly, activation, and checkout of the assist with the assembly, activation, and checkout of the assist with the assembly, activation, and checkout of the Kibo component. Kibo component. Kibo component. The ELM-PS is a Kibo storage facility that provides stow- The ELM-PS is a Kibo storage facility that provides stow- The ELM-PS is a Kibo storage facility that provides stow- age space for experiment payloads, samples, and spare age space for experiment payloads, samples, and spare age space for experiment payloads, samples, and spare items. The ELM-PS measures 14.4 feet (4.4 meters) wide items. The ELM-PS measures 14.4 feet (4.4 meters) wide items. The ELM-PS measures 14.4 feet (4.4 meters) wide and 13.8 feet (4.2 meters) long. Up to eight racks can be and 13.8 feet (4.2 meters) long. Up to eight racks can be and 13.8 feet (4.2 meters) long. Up to eight racks can be housed in the ELM-PS. The pressurized interior of the housed in the ELM-PS. The pressurized interior of the housed in the ELM-PS. The pressurized interior of the ELM-PS is maintained at one atmosphere, thus providing ELM-PS is maintained at one atmosphere, thus providing ELM-PS is maintained at one atmosphere, thus providing a room-temperature working environment. The crew can a room-temperature working environment. The crew can a room-temperature working environment. The crew can freely move between the ELM-PS and the main experiment freely move between the ELM-PS and the main experiment freely move between the ELM-PS and the main experiment module, the Pressurized Module (PM). module, the Pressurized Module (PM). module, the Pressurized Module (PM).

B-22 B-22 B-22 During STS-123, the ELM-PS was attached to the zenith During STS-123, the ELM-PS was attached to the zenith During STS-123, the ELM-PS was attached to the zenith port on top of Harmony, the Node 2 module. The ELM-PS port on top of Harmony, the Node 2 module. The ELM-PS port on top of Harmony, the Node 2 module. The ELM-PS remained attached to the Harmony module until the PM remained attached to the Harmony module until the PM remained attached to the Harmony module until the PM was delivered on space shuttle mission STS-124. The final was delivered on space shuttle mission STS-124. The final was delivered on space shuttle mission STS-124. The final location of the ELM-PS is on the top port of the PM. location of the ELM-PS is on the top port of the PM. location of the ELM-PS is on the top port of the PM. The Pressurized Module—the central part of Kibo—and The Pressurized Module—the central part of Kibo—and The Pressurized Module—the central part of Kibo—and Japanese Experiment Module Remote Manipulator System Japanese Experiment Module Remote Manipulator System Japanese Experiment Module Remote Manipulator System (JEMRMS) was launched on the STS-124/1J mission. At (JEMRMS) was launched on the STS-124/1J mission. At (JEMRMS) was launched on the STS-124/1J mission. At 36.7 feet (11.2 meters) long and 14.4 feet (4.4 meters) wide, 36.7 feet (11.2 meters) long and 14.4 feet (4.4 meters) wide, 36.7 feet (11.2 meters) long and 14.4 feet (4.4 meters) wide, the PM is the station’s largest science laboratory. The pres- the PM is the station’s largest science laboratory. The pres- the PM is the station’s largest science laboratory. The pres- surized interior of the PM is maintained at one atmosphere surized interior of the PM is maintained at one atmosphere surized interior of the PM is maintained at one atmosphere to provide a room-temperature working environment. The to provide a room-temperature working environment. The to provide a room-temperature working environment. The ISS crew conducts unique microgravity experiments within ISS crew conducts unique microgravity experiments within ISS crew conducts unique microgravity experiments within the PM laboratory. The PM holds 23 racks, 10 of which the PM laboratory. The PM holds 23 racks, 10 of which the PM laboratory. The PM holds 23 racks, 10 of which are International Standard Payload Racks designed for are International Standard Payload Racks designed for are International Standard Payload Racks designed for experiment payloads. experiment payloads. experiment payloads.

Seen from space shuttle Discovery, mission STS-124, the Seen from space shuttle Discovery, mission STS-124, the Seen from space shuttle Discovery, mission STS-124, the newly installed Kibo JEM-PM is attached to the port side newly installed Kibo JEM-PM is attached to the port side newly installed Kibo JEM-PM is attached to the port side of the Harmony node. The Kibo ELM-PS and JEMRMS are of the Harmony node. The Kibo ELM-PS and JEMRMS are of the Harmony node. The Kibo ELM-PS and JEMRMS are visible at center. visible at center. visible at center.

Kibo’s robotic arm, or JEMRMS, serves as an extension Kibo’s robotic arm, or JEMRMS, serves as an extension Kibo’s robotic arm, or JEMRMS, serves as an extension of the human hand and arm in manipulating experiments of the human hand and arm in manipulating experiments of the human hand and arm in manipulating experiments on the EF and enables operation of exposed experiments on the EF and enables operation of exposed experiments on the EF and enables operation of exposed experiments without the assistance of a spacewalking crew. The JEM- without the assistance of a spacewalking crew. The JEM- without the assistance of a spacewalking crew. The JEM- RMS is composed of the Main Arm and the Small Fine Arm, RMS is composed of the Main Arm and the Small Fine Arm, RMS is composed of the Main Arm and the Small Fine Arm, both of which have six articulating joints. The Main Arm both of which have six articulating joints. The Main Arm both of which have six articulating joints. The Main Arm is used for exchanging EF payloads and for moving large is used for exchanging EF payloads and for moving large is used for exchanging EF payloads and for moving large items. The Small Fine Arm, which attaches to the end of items. The Small Fine Arm, which attaches to the end of items. The Small Fine Arm, which attaches to the end of the Main Arm, is used for more delicate tasks. The crew the Main Arm, is used for more delicate tasks. The crew the Main Arm, is used for more delicate tasks. The crew operates these robotic arms from the JEMRMS Console operates these robotic arms from the JEMRMS Console operates these robotic arms from the JEMRMS Console located in the PM. located in the PM. located in the PM. The Exposed Facility (EF) and Experiment Logistics Mod- The Exposed Facility (EF) and Experiment Logistics Mod- The Exposed Facility (EF) and Experiment Logistics Mod- ule–Exposed Section (ELM–ES) was launched on the STS- ule–Exposed Section (ELM–ES) was launched on the STS- ule–Exposed Section (ELM–ES) was launched on the STS- 127/2J/A mission. The EF provides a multipurpose platform 127/2J/A mission. The EF provides a multipurpose platform 127/2J/A mission. The EF provides a multipurpose platform where 10 science experiment and system payloads can be where 10 science experiment and system payloads can be where 10 science experiment and system payloads can be deployed and operated in the unpressurized environment deployed and operated in the unpressurized environment deployed and operated in the unpressurized environment of space. The EF measures 18.4 feet (5.6 meters) wide, of space. The EF measures 18.4 feet (5.6 meters) wide, of space. The EF measures 18.4 feet (5.6 meters) wide, 16.4 feet (5 meters) high, and 13.1 feet (4 meters) long. The 16.4 feet (5 meters) high, and 13.1 feet (4 meters) long. The 16.4 feet (5 meters) high, and 13.1 feet (4 meters) long. The experiment payloads attached to the EF are exchanged experiment payloads attached to the EF are exchanged experiment payloads attached to the EF are exchanged using the JEMRMS. The ELM-ES is a pallet that can hold using the JEMRMS. The ELM-ES is a pallet that can hold using the JEMRMS. The ELM-ES is a pallet that can hold

B-23 B-23 B-23 three experiment payloads, measures 16.1 feet (4.9 me- three experiment payloads, measures 16.1 feet (4.9 me- three experiment payloads, measures 16.1 feet (4.9 me- ters) wide, 7.2 feet (2.2 meters) high, and 13.8 feet (4.2 ters) wide, 7.2 feet (2.2 meters) high, and 13.8 feet (4.2 ters) wide, 7.2 feet (2.2 meters) high, and 13.8 feet (4.2 meters) long, and is attached to the end of the EF. meters) long, and is attached to the end of the EF. meters) long, and is attached to the end of the EF.

A close-up view of the Japanese Experiment Module– A close-up view of the Japanese Experiment Module– A close-up view of the Japanese Experiment Module– Exposed Facility and Kibo laboratory of the ISS photo- Exposed Facility and Kibo laboratory of the ISS photo- Exposed Facility and Kibo laboratory of the ISS photo- graphed by an STS-127 crew member while space shuttle graphed by an STS-127 crew member while space shuttle graphed by an STS-127 crew member while space shuttle Endeavour was docked with the space station Endeavour was docked with the space station Endeavour was docked with the space station

B-24 B-24 B-24 Mini-Research Module 2 Mini-Research Module 2 Mini-Research Module 2

Mini-Research Module 2 (MRM2)—named "Poisk," Russian Mini-Research Module 2 (MRM2)—named "Poisk," Russian Mini-Research Module 2 (MRM2—named "Poisk," Russian for “Search”—is a new Russian module that arrived at the for “Search”—is a new Russian module that arrived at the for “Search”—is a new Russian module that arrived at the ISS early in the Expedition 21 increment. It was launched ISS early in the Expedition 21 increment. It was launched ISS early in the Expedition 21 increment. It was launched on November 10, 2009, from the Baikonur Cosmodrome, on November 10, 2009, from the Baikonur Cosmodrome, on November 10, 2009, from the Baikonur Cosmodrome, Kazakhstan, on a Russian Soyuz rocket and docked to the Kazakhstan, on a Russian Soyuz rocket and docked to the Kazakhstan, on a Russian Soyuz rocket and docked to the space-facing port of the Zvezda service module. space-facing port of the Zvezda service module. space-facing port of the Zvezda service module.

Developed at RSC Energia, MRM2 doubles as an addition- Developed at RSC Energia, MRM2 doubles as an addition- Developed at RSC Energia, MRM2 doubles as an addition- al airlock for EVAs and as a docking port for arriving Rus- al airlock for EVAs and as a docking port for arriving Rus- al airlock for EVAs and as a docking port for arriving Rus- sian vehicles to the space station. The module increases sian vehicles to the space station. The module increases sian vehicles to the space station. The module increases the number of ports on the Russian segment of the station the number of ports on the Russian segment of the station the number of ports on the Russian segment of the station and enables the subsequent addition of another larger and enables the subsequent addition of another larger and enables the subsequent addition of another larger module to the Russian segment. MRM2 also provides a module to the Russian segment. MRM2 also provides a module to the Russian segment. MRM2 also provides a docking target for visual monitoring of automated Soyuz docking target for visual monitoring of automated Soyuz docking target for visual monitoring of automated Soyuz and Progress vehicle dockings and offers pressurized and Progress vehicle dockings and offers pressurized and Progress vehicle dockings and offers pressurized volume for stowing cargo and scientific hardware. volume for stowing cargo and scientific hardware. volume for stowing cargo and scientific hardware.

On its flight to the station, MRM2 carried 1,764 lb (800 kg) On its flight to the station, MRM2 carried 1,764 lb (800 kg) On its flight to the station, MRM2 carried 1,764 lb (800 kg) of cargo in its pressurized compartment consisting of Rus- of cargo in its pressurized compartment consisting of Rus- of cargo in its pressurized compartment consisting of Rus- sian Orlan spacesuits and life support equipment. sian Orlan spacesuits and life support equipment. sian Orlan spacesuits and life support equipment. Length: 13 ft, 3 in (4.049 m) Length: 13 ft, 3 in (4.049 m) Length: 13 ft, 3 in (4.049 m) Diameter: 8 ft, 4 in (2.55 m) Diameter: 8 ft, 4 in (2.55 m) Diameter: 8 ft, 4 in (2.55 m) Weight: 8,201 lb (3,720 kg) Weight: 8,201 lb (3,720 kg) Weight: 8,201 lb (3,720 kg) Habitable volume: 380 ft3 (10.7 m3) Habitable volume: 380 ft3 (10.7 m3) Habitable volume: 380 ft3 (10.7 m3) Pressurized volume: 523 ft3 (14.8 m3) Pressurized volume: 523 ft3 (14.8 m3) Pressurized volume: 523 ft3 (14.8 m3)

Cargo Cargo Cargo Boom Boom Boom EVA EVA EVA Hatch Hatch Hatch

Scientific Scientific Scientific Hardware Hardware Hardware

Mini-Research Module 2 External Features Mini-Research Module 2 External Features Mini-Research Module 2 External Features

B-25 B-25 B-25 Pressurized Mating Adapters (PMAs) Pressurized Mating Adapters (PMAs) Pressurized Mating Adapters (PMAs)

Conical docking adapters, called pressurized mating Conical docking adapters, called pressurized mating Conical docking adapters, called pressurized mating adapters (PMAs), allow the docking systems used by the adapters (PMAs), allow the docking systems used by the adapters (PMAs), allow the docking systems used by the space shuttle and by Russian modules to attach to the space shuttle and by Russian modules to attach to the space shuttle and by Russian modules to attach to the ISS. The ISS uses three PMAs to interconnect spacecraft ISS. The ISS uses three PMAs to interconnect spacecraft ISS. The ISS uses three PMAs to interconnect spacecraft and modules with different docking mechanisms. The first and modules with different docking mechanisms. The first and modules with different docking mechanisms. The first two PMAs were launched with the Unity module in 1998 two PMAs were launched with the Unity module in 1998 two PMAs were launched with the Unity module in 1998 aboard STS-88. The third was launched in 2000 aboard aboard STS-88. The third was launched in 2000 aboard aboard STS-88. The third was launched in 2000 aboard STS-92. PMA-2 is currently mounted on the forward port STS-92. PMA-2 is currently mounted on the forward port STS-92. PMA-2 is currently mounted on the forward port of the Harmony connecting node and is used when space of the Harmony connecting node and is used when space of the Harmony connecting node and is used when space shuttle orbiters dock at the station. Airtight seals are shuttle orbiters dock at the station. Airtight seals are shuttle orbiters dock at the station. Airtight seals are formed by devices that pull together, lock, and seal—a formed by devices that pull together, lock, and seal—a formed by devices that pull together, lock, and seal—a different method than the “bump-to-trip latch, then seal” different method than the “bump-to-trip latch, then seal” different method than the “bump-to-trip latch, then seal” procedure that most spacecraft use to dock. The tight seal procedure that most spacecraft use to dock. The tight seal procedure that most spacecraft use to dock. The tight seal that permits shirt-sleeved transit between ISS elements that permits shirt-sleeved transit between ISS elements that permits shirt-sleeved transit between ISS elements and spacecraft is provided in part by common berthing and spacecraft is provided in part by common berthing and spacecraft is provided in part by common berthing mechanism technology. PMAs are Boeing products, built mechanism technology. PMAs are Boeing products, built mechanism technology. PMAs are Boeing products, built in Huntington Beach, Calif. in Huntington Beach, Calif. in Huntington Beach, Calif. Length: 7 ft (2.13 m) Length: 7 ft (2.13 m) Length: 7 ft (2.13 m) Diameter: 5 ft (1.5 m) at one end, Diameter: 5 ft (1.5 m) at one end, Diameter: 5 ft (1.5 m) at one end, 9 ft (2.74 m) at the other 9 ft (2.74 m) at the other 9 ft (2.74 m) at the other Material: Aluminum pressure shell Material: Aluminum pressure shell Material: Aluminum pressure shell with an aluminum debris with an aluminum debris with an aluminum debris shield shield shield Joint Airlock “Quest” Joint Airlock “Quest” Joint Airlock “Quest”

The Joint Airlock module, which has the capability to be The Joint Airlock module, which has the capability to be The Joint Airlock module, which has the capability to be used by both Russian and U.S. spacesuit designs, con- used by both Russian and U.S. spacesuit designs, con- used by both Russian and U.S. spacesuit designs, con- sists of two sections, a crew lock that is used to exit the sists of two sections, a crew lock that is used to exit the sists of two sections, a crew lock that is used to exit the station and begin a spacewalk, and an equipment lock station and begin a spacewalk, and an equipment lock station and begin a spacewalk, and an equipment lock used for storing gear. used for storing gear. used for storing gear. Length: 18 ft (5.5 m) Length: 18 ft (5.5 m) Length: 18 ft (5.5 m) Diameter: 13 ft (4 m) Diameter: 13 ft (4 m) Diameter: 13 ft (4 m) Weight: 20,831 lb (9,449 kg) Weight: 20,831 lb (9,449 kg) Weight: 20,831 lb (9,449 kg) Volume: 1,200 ft3 (34 m3) Volume: 1,200 ft3 (34 m3) Volume: 1,200 ft3 (34 m3) Material: Aluminum, covered with Material: Aluminum, covered with Material: Aluminum, covered with insulation blankets and insulation blankets and insulation blankets and intermediate debris shields intermediate debris shields intermediate debris shields Number of racks: Two systems racks Number of racks: Two systems racks Number of racks: Two systems racks Delivered: Space shuttle mission Delivered: Space shuttle mission Delivered: Space shuttle mission STS-104/ISS-7A STS-104/ISS-7A STS-104/ISS-7A Joint Airlock “Quest” Confi guration Joint Airlock “Quest” Confi guration Joint Airlock “Quest” Confi guration

Power Supply Assembly (PSA) Battery Charging Assembly (BCA) Power Supply Assembly (PSA) Battery Charging Assembly (BCA) Power Supply Assembly (PSA) Battery Charging Assembly (BCA) In-Flight Refill Unit (IRU) In-Flight Refill Unit (IRU) In-Flight Refill Unit (IRU) Battery Stowage EMU Water Recharge Bag Battery Stowage EMU Water Recharge Bag Battery Stowage EMU Water Recharge Bag Assembly (BSA) Assembly (BSA) Assembly (BSA)

Equipment Crew Equipment Crew Equipment Crew Lock (E/L) Lock (C/L) Lock (E/L) Lock (C/L) Lock (E/L) Lock (C/L)

Don/Doff Don/Doff Don/Doff EV Hatch EV Hatch EV Hatch Assembly Assembly Assembly Umbilical Interface Umbilical Interface Umbilical Interface IV Hatch Assembly (UIA) IV Hatch Assembly (UIA) IV Hatch Assembly (UIA)

B-26 B-26 B-26 Pirs Docking Compartment Pirs Docking Compartment Pirs Docking Compartment

The Pirs docking compartment is attached to the bottom, The Pirs docking compartment is attached to the bottom, The Pirs docking compartment is attached to the bottom, Earth-facing port of the Zvezda service module. It was Earth-facing port of the Zvezda service module. It was Earth-facing port of the Zvezda service module. It was launched on a Russian Soyuz rocket on Sept. 14, 2001, and launched on a Russian Soyuz rocket on Sept. 14, 2001, and launched on a Russian Soyuz rocket on Sept. 14, 2001, and configured during three spacewalks by the Expedition 3 configured during three spacewalks by the Expedition 3 configured during three spacewalks by the Expedition 3 crew. crew. crew.

Video-recorded by one of the Expedition 3 crew members, Video-recorded by one of the Expedition 3 crew members, Video-recorded by one of the Expedition 3 crew members, Pirs docks with the ISS on Sept. 16, 2001. Pirs docks with the ISS on Sept. 16, 2001. Pirs docks with the ISS on Sept. 16, 2001.

Pirs, Russian for “pier,” has two primary functions. It serves Pirs, Russian for “pier,” has two primary functions. It serves Pirs, Russian for “pier,” has two primary functions. It serves as a docking port for transport and cargo vehicles to as a docking port for transport and cargo vehicles to as a docking port for transport and cargo vehicles to the ISS and as an airlock for the performance of space- the ISS and as an airlock for the performance of space- the ISS and as an airlock for the performance of space- walks by two station crew members using Russian Orlan walks by two station crew members using Russian Orlan walks by two station crew members using Russian Orlan spacesuits. spacesuits. spacesuits. In addition, the docking compartment can transport fuel In addition, the docking compartment can transport fuel In addition, the docking compartment can transport fuel from the fuel tanks of a docked Progress resupply vehicle from the fuel tanks of a docked Progress resupply vehicle from the fuel tanks of a docked Progress resupply vehicle to either the Zvezda or the Zarya. It can also transfer pro- to either the Zvezda or the Zarya. It can also transfer pro- to either the Zvezda or the Zarya. It can also transfer pro- pellant from the Zvezda and Zarya to the propulsion system pellant from the Zvezda and Zarya to the propulsion system pellant from the Zvezda and Zarya to the propulsion system of docked vehicles—Soyuz and Progress. of docked vehicles—Soyuz and Progress. of docked vehicles—Soyuz and Progress. Length: 16 ft (4.91 m) Length: 16 ft (4.91 m) Length: 16 ft (4.91 m) Width: 8.4 ft (2.55 m) Width: 8.4 ft (2.55 m) Width: 8.4 ft (2.55 m) Weight: 7,150 lb (3,243 kg) Weight: 7,150 lb (3,243 kg) Weight: 7,150 lb (3,243 kg)

Zenith 1 (Z1) Truss Zenith 1 (Z1) Truss Zenith 1 (Z1) Truss The first truss piece, the Z1 truss, was launched on STS- The first truss piece, the Z1 truss, was launched on STS- The first truss piece, the Z1 truss, was launched on STS- 92 and subsequently permanently attached during space 92 and subsequently permanently attached during space 92 and subsequently permanently attached during space shuttle mission STS-97. Although not a part of the main shuttle mission STS-97. Although not a part of the main shuttle mission STS-97. Although not a part of the main truss, the Z1 truss was the first permanent lattice-work truss, the Z1 truss was the first permanent lattice-work truss, the Z1 truss was the first permanent lattice-work structure for the ISS, very much like a girder, setting the structure for the ISS, very much like a girder, setting the structure for the ISS, very much like a girder, setting the stage for the future addition of the station’s major trusses. stage for the future addition of the station’s major trusses. stage for the future addition of the station’s major trusses. It is unpressurized but features two common berthing It is unpressurized but features two common berthing It is unpressurized but features two common berthing mechanism docking ports for easy connecting and data mechanism docking ports for easy connecting and data mechanism docking ports for easy connecting and data communications. Originally used as a temporary mount- communications. Originally used as a temporary mount- communications. Originally used as a temporary mount- ing position for the P6 truss and solar array, the Z1 solely ing position for the P6 truss and solar array, the Z1 solely ing position for the P6 truss and solar array, the Z1 solely houses control moment gyroscopes (CMGs) for stabili- houses control moment gyroscopes (CMGs) for stabili- houses control moment gyroscopes (CMGs) for stabili- zation and orientation and communications systems. It zation and orientation and communications systems. It zation and orientation and communications systems. It is also equipped with several spacewalk aids: EVA tool is also equipped with several spacewalk aids: EVA tool is also equipped with several spacewalk aids: EVA tool stowage devices (ETSDs), grapple fixture, and handholds stowage devices (ETSDs), grapple fixture, and handholds stowage devices (ETSDs), grapple fixture, and handholds and handrails. and handrails. and handrails.

B-27 B-27 B-27 STS-92/ISS-3A astronauts work with the antenna on the STS-92/ISS-3A astronauts work with the antenna on the STS-92/ISS-3A astronauts work with the antenna on the newly deployed Z1 truss structure. newly deployed Z1 truss structure. newly deployed Z1 truss structure. Length: 16.1 ft (4.9 m) Length: 16.1 ft (4.9 m) Length: 16.1 ft (4.9 m) Width: 13.8 ft (4.2 m) Width: 13.8 ft (4.2 m) Width: 13.8 ft (4.2 m) Weight: 19,227 lb (8,721 kg) Weight: 19,227 lb (8,721 kg) Weight: 19,227 lb (8,721 kg) Starboard 0 (S0) Truss Starboard 0 (S0) Truss Starboard 0 (S0) Truss The central integrated truss (starboard 0) forms the center The central integrated truss (starboard 0) forms the center The central integrated truss (starboard 0) forms the center backbone of the ISS. It is attached to the U.S. Laboratory backbone of the ISS. It is attached to the U.S. Laboratory backbone of the ISS. It is attached to the U.S. Laboratory and is used to route power to the pressurized station and is used to route power to the pressurized station and is used to route power to the pressurized station modules and conduct heat away from the modules to the modules and conduct heat away from the modules to the modules and conduct heat away from the modules to the S1 and P1 trusses. S1 and P1 trusses. S1 and P1 trusses. The truss segments were numbered in ascending order The truss segments were numbered in ascending order The truss segments were numbered in ascending order outward to the port and starboard sides. At one time, an S2 outward to the port and starboard sides. At one time, an S2 outward to the port and starboard sides. At one time, an S2 and P2 were planned but were eliminated when the station and P2 were planned but were eliminated when the station and P2 were planned but were eliminated when the station design was scaled back. From S0, the truss segments are design was scaled back. From S0, the truss segments are design was scaled back. From S0, the truss segments are P1, P3, P4, P5, and P6; and S1, S3, S4, S5, and S6. P1, P3, P4, P5, and P6; and S1, S3, S4, S5, and S6. P1, P3, P4, P5, and P6; and S1, S3, S4, S5, and S6.

Central integrated truss (S0) following installation during Central integrated truss (S0) following installation during Central integrated truss (S0) following installation during space shuttle mission STS-110/ISS-8A space shuttle mission STS-110/ISS-8A space shuttle mission STS-110/ISS-8A Length: 44 ft (13.4 m) Length: 44 ft (13.4 m) Length: 44 ft (13.4 m) Width: 15 ft (4.6 m) Width: 15 ft (4.6 m) Width: 15 ft (4.6 m) Weight: 24,890 lb (11,290 kg) Weight: 24,890 lb (11,290 kg) Weight: 24,890 lb (11,290 kg)

B-28 B-28 B-28 Starboard 1 (S1) Truss Starboard 1 (S1) Truss Starboard 1 (S1) Truss

The S1 truss, the first starboard truss segment, was at- The S1 truss, the first starboard truss segment, was at- The S1 truss, the first starboard truss segment, was at- tached to the starboard side of the S0 truss on Oct. 10, tached to the starboard side of the S0 truss on Oct. 10, tached to the starboard side of the S0 truss on Oct. 10, 2002. The S1 truss provides structural support for the 2002. The S1 truss provides structural support for the 2002. The S1 truss provides structural support for the Active Thermal Control System, Mobile Transporter, and Active Thermal Control System, Mobile Transporter, and Active Thermal Control System, Mobile Transporter, and a Crew and Equipment Translation Aid cart. The cart is a Crew and Equipment Translation Aid cart. The cart is a Crew and Equipment Translation Aid cart. The cart is manually operated by a spacewalker and can also be manually operated by a spacewalker and can also be manually operated by a spacewalker and can also be used as a work platform. The cooling system is like the used as a work platform. The cooling system is like the used as a work platform. The cooling system is like the one in a car radiator except that it uses 99.9 percent pure one in a car radiator except that it uses 99.9 percent pure one in a car radiator except that it uses 99.9 percent pure ammonia, compared to 1 percent in household products. ammonia, compared to 1 percent in household products. ammonia, compared to 1 percent in household products. The Thermal Radiator Rotary Joint rotates the three radiator The Thermal Radiator Rotary Joint rotates the three radiator The Thermal Radiator Rotary Joint rotates the three radiator structures that contain eight panels each in a 105-degree structures that contain eight panels each in a 105-degree structures that contain eight panels each in a 105-degree span either way to keep the three radiators’ panels in the span either way to keep the three radiators’ panels in the span either way to keep the three radiators’ panels in the shade; it also transfers power and ammonia to the radia- shade; it also transfers power and ammonia to the radia- shade; it also transfers power and ammonia to the radia- tors. In addition, the S1 truss has mounts for cameras and tors. In addition, the S1 truss has mounts for cameras and tors. In addition, the S1 truss has mounts for cameras and lights, as well as antenna support equipment for S-band lights, as well as antenna support equipment for S-band lights, as well as antenna support equipment for S-band communications equipment. Detailed design, test, and communications equipment. Detailed design, test, and communications equipment. Detailed design, test, and construction of the S1 structure were conducted by Boeing construction of the S1 structure were conducted by Boeing construction of the S1 structure were conducted by Boeing in Huntington Beach, Calif. in Huntington Beach, Calif. in Huntington Beach, Calif.

S1 truss being installed during space shuttle mission S1 truss being installed during space shuttle mission S1 truss being installed during space shuttle mission STS-112/ISS-9A STS-112/ISS-9A STS-112/ISS-9A

Length: 45 ft (13.7 m) Length: 45 ft (13.7 m) Length: 45 ft (13.7 m) Width: 15 ft (4.6 m) Width: 15 ft (4.6 m) Width: 15 ft (4.6 m) Weight: 31,137 lb (14,124 kg) Weight: 31,137 lb (14,124 kg) Weight: 31,137 lb (14,124 kg)

B-29 B-29 B-29 Port 1 (P1) Truss Port 1 (P1) Truss Port 1 (P1) Truss

The P1 truss, the first port truss segment, was attached The P1 truss, the first port truss segment, was attached The P1 truss, the first port truss segment, was attached to the port side of the S0 truss on Nov. 26, 2002. The P1 to the port side of the S0 truss on Nov. 26, 2002. The P1 to the port side of the S0 truss on Nov. 26, 2002. The P1 truss provides structural support for the Active Thermal truss provides structural support for the Active Thermal truss provides structural support for the Active Thermal Control System, Mobile Transporter, and a second Crew Control System, Mobile Transporter, and a second Crew Control System, Mobile Transporter, and a second Crew and Equipment Translation Aid cart. The cart is manually and Equipment Translation Aid cart. The cart is manually and Equipment Translation Aid cart. The cart is manually operated by a spacewalker and can also be used as a operated by a spacewalker and can also be used as a operated by a spacewalker and can also be used as a work platform. The cooling system is like a car radiator work platform. The cooling system is like a car radiator work platform. The cooling system is like a car radiator except that it uses 99.9 percent pure ammonia, compared except that it uses 99.9 percent pure ammonia, compared except that it uses 99.9 percent pure ammonia, compared to 1 percent in household products. The Thermal Radia- to 1 percent in household products. The Thermal Radia- to 1 percent in household products. The Thermal Radia- tor Rotary Joint rotates the three radiator structures that tor Rotary Joint rotates the three radiator structures that tor Rotary Joint rotates the three radiator structures that contain eight panels each in a 105-degree span either contain eight panels each in a 105-degree span either contain eight panels each in a 105-degree span either way to keep the three radiators’ panels in the shade; it way to keep the three radiators’ panels in the shade; it way to keep the three radiators’ panels in the shade; it also transfers power and ammonia to the radiators. In also transfers power and ammonia to the radiators. In also transfers power and ammonia to the radiators. In addition, the P1 truss has mounts for cameras and lights, addition, the P1 truss has mounts for cameras and lights, addition, the P1 truss has mounts for cameras and lights, as well as antenna support equipment for both UHF and as well as antenna support equipment for both UHF and as well as antenna support equipment for both UHF and S-band communications equipment. The S-band equip- S-band communications equipment. The S-band equip- S-band communications equipment. The S-band equip- ment is currently on the P6 truss. Detailed design, test, ment is currently on the P6 truss. Detailed design, test, ment is currently on the P6 truss. Detailed design, test, and construction of the P1 structure were conducted by and construction of the P1 structure were conducted by and construction of the P1 structure were conducted by Boeing in Huntington Beach, Calif. Boeing in Huntington Beach, Calif. Boeing in Huntington Beach, Calif.

P1 truss being installed during space shuttle mission P1 truss being installed during space shuttle mission P1 truss being installed during space shuttle mission STS-113/ISS-11A STS-113/ISS-11A STS-113/ISS-11A

Length: 45 ft (13.7 m) Length: 45 ft (13.7 m) Length: 45 ft (13.7 m) Width: 15 ft (4.6 m) Width: 15 ft (4.6 m) Width: 15 ft (4.6 m) Weight: 30,871 lb (14,003 kg) Weight: 30,871 lb (14,003 kg) Weight: 30,871 lb (14,003 kg)

B-30 B-30 B-30 Starboard 3 and 4 (S3/S4) Trusses Starboard 3 and 4 (S3/S4) Trusses Starboard 3 and 4 (S3/S4) Trusses

The starboard 3 and 4 (S3/S4) truss segments are the The starboard 3 and 4 (S3/S4) truss segments are the The starboard 3 and 4 (S3/S4) truss segments are the largest and heaviest space station payload. The principal largest and heaviest space station payload. The principal largest and heaviest space station payload. The principal functions of the S3 and S4 truss segments are to provide functions of the S3 and S4 truss segments are to provide functions of the S3 and S4 truss segments are to provide electrical power and data interfaces for future mission electrical power and data interfaces for future mission electrical power and data interfaces for future mission payloads and convert sunlight to electricity. The segments payloads and convert sunlight to electricity. The segments payloads and convert sunlight to electricity. The segments include another set of solar array wings (SAWs) and a include another set of solar array wings (SAWs) and a include another set of solar array wings (SAWs) and a second solar alpha rotary joint (SARJ), which keeps the second solar alpha rotary joint (SARJ), which keeps the second solar alpha rotary joint (SARJ), which keeps the arrays permanently pointed toward the sun. arrays permanently pointed toward the sun. arrays permanently pointed toward the sun.

Designed by The Boeing Company, the S3/S4 truss seg- Designed by The Boeing Company, the S3/S4 truss seg- Designed by The Boeing Company, the S3/S4 truss seg- ments, which are attached to the S1 truss, are the second ments, which are attached to the S1 truss, are the second ments, which are attached to the S1 truss, are the second starboard addition to the 11-segment integrated truss starboard addition to the 11-segment integrated truss starboard addition to the 11-segment integrated truss structure that spans more than 300 feet to carry power, structure that spans more than 300 feet to carry power, structure that spans more than 300 feet to carry power, data, and temperature control for the orbital outpost’s elec- data, and temperature control for the orbital outpost’s elec- data, and temperature control for the orbital outpost’s elec- tronics. Beside two SAWs and a SARJ, the S3/S4 structure tronics. Beside two SAWs and a SARJ, the S3/S4 structure tronics. Beside two SAWs and a SARJ, the S3/S4 structure has several distinct elements: the integrated equipment has several distinct elements: the integrated equipment has several distinct elements: the integrated equipment assembly (IEA), two beta gimbal assemblies (BGAs), and assembly (IEA), two beta gimbal assemblies (BGAs), and assembly (IEA), two beta gimbal assemblies (BGAs), and the photovoltaic thermal control subsystem (PVTCS). the photovoltaic thermal control subsystem (PVTCS). the photovoltaic thermal control subsystem (PVTCS).

Backdropped by the blackness of space, the ISS is shown Backdropped by the blackness of space, the ISS is shown Backdropped by the blackness of space, the ISS is shown in its expanded configuration after the installation of the in its expanded configuration after the installation of the in its expanded configuration after the installation of the S3/S4 truss during space shuttle mission STS-117/ISS- S3/S4 truss during space shuttle mission STS-117/ISS- S3/S4 truss during space shuttle mission STS-117/ISS- 13A. 13A. 13A.

The major S3 subsystems include the SARJ, segment- The major S3 subsystems include the SARJ, segment- The major S3 subsystems include the SARJ, segment- to-segment attach system (SSAS), and payload attach to-segment attach system (SSAS), and payload attach to-segment attach system (SSAS), and payload attach system (PAS). The S3 truss segment provides mechanical, system (PAS). The S3 truss segment provides mechanical, system (PAS). The S3 truss segment provides mechanical, power, and data interfaces to payloads attached to the power, and data interfaces to payloads attached to the power, and data interfaces to payloads attached to the four PAS platforms, axial indexing for solar tracking via four PAS platforms, axial indexing for solar tracking via four PAS platforms, axial indexing for solar tracking via the SARJ, translation and work site accommodations for the SARJ, translation and work site accommodations for the SARJ, translation and work site accommodations for the mobile transporter, and accommodations for ammonia the mobile transporter, and accommodations for ammonia the mobile transporter, and accommodations for ammonia servicing of the outboard PV modules and two multiplexer/ servicing of the outboard PV modules and two multiplexer/ servicing of the outboard PV modules and two multiplexer/ demuliplexers (MDMs). The MDMs are basically comput- demuliplexers (MDMs). The MDMs are basically comput- demuliplexers (MDMs). The MDMs are basically comput- ers that tell other electrical components when to turn on ers that tell other electrical components when to turn on ers that tell other electrical components when to turn on and off and monitor hardware. The S3 also provides a and off and monitor hardware. The S3 also provides a and off and monitor hardware. The S3 also provides a passive attachment point to the S1 segment via the SSAS passive attachment point to the S1 segment via the SSAS passive attachment point to the S1 segment via the SSAS and pass through of power and data to and from the and pass through of power and data to and from the and pass through of power and data to and from the outboard segments. outboard segments. outboard segments.

B-31 B-31 B-31 Major subsystems of the S4 truss are the port inboard Major subsystems of the S4 truss are the port inboard Major subsystems of the S4 truss are the port inboard photovoltaic module (PVM), the photovoltaic radiator photovoltaic module (PVM), the photovoltaic radiator photovoltaic module (PVM), the photovoltaic radiator (PVR), the alpha joint interface structure (AJIS), and the (PVR), the alpha joint interface structure (AJIS), and the (PVR), the alpha joint interface structure (AJIS), and the modified Rocketdyne truss attachment system (MRTAS). modified Rocketdyne truss attachment system (MRTAS). modified Rocketdyne truss attachment system (MRTAS). The S4 PVM includes all equipment outboard of the SARJ The S4 PVM includes all equipment outboard of the SARJ The S4 PVM includes all equipment outboard of the SARJ outboard bulkhead, namely the two photovoltaic array outboard bulkhead, namely the two photovoltaic array outboard bulkhead, namely the two photovoltaic array assemblies (PVAAs) and the IEA. The PVR provides ther- assemblies (PVAAs) and the IEA. The PVR provides ther- assemblies (PVAAs) and the IEA. The PVR provides ther- mal cooling for the IEA. The AJIS provides the structural mal cooling for the IEA. The AJIS provides the structural mal cooling for the IEA. The AJIS provides the structural transition between S3 and S4. Each PVAA consists of a transition between S3 and S4. Each PVAA consists of a transition between S3 and S4. Each PVAA consists of a SAW and BGA. The S4 also contains the passive side of SAW and BGA. The S4 also contains the passive side of SAW and BGA. The S4 also contains the passive side of the MRTAS that will provide the structural attachment for the MRTAS that will provide the structural attachment for the MRTAS that will provide the structural attachment for the S5 truss. the S5 truss. the S5 truss. Length: 44.8 ft (13.7 m) Length: 44.8 ft (13.7 m) Length: 44.8 ft (13.7 m) Width: 16.3 ft (5 m) Width: 16.3 ft (5 m) Width: 16.3 ft (5 m) Weight: 35,678 lb (16,183 kg) Weight: 35,678 lb (16,183 kg) Weight: 35,678 lb (16,183 kg)

Port 3 and 4 (P3/P4) Trusses Port 3 and 4 (P3/P4) Trusses Port 3 and 4 (P3/P4) Trusses The port 3 and 4 (P3/P4) trusses are attached to the P1 The port 3 and 4 (P3/P4) trusses are attached to the P1 The port 3 and 4 (P3/P4) trusses are attached to the P1 truss and provide an attachment point for P5. The P3 and truss and provide an attachment point for P5. The P3 and truss and provide an attachment point for P5. The P3 and P4 trusses also provide a second set of solar array wings P4 trusses also provide a second set of solar array wings P4 trusses also provide a second set of solar array wings (SAWs) and the first alpha joint. Each solar wing, deployed (SAWs) and the first alpha joint. Each solar wing, deployed (SAWs) and the first alpha joint. Each solar wing, deployed in opposite directions from each other, is 115 feet by 38 in opposite directions from each other, is 115 feet by 38 in opposite directions from each other, is 115 feet by 38 feet. The segments support utility routing, power distribu- feet. The segments support utility routing, power distribu- feet. The segments support utility routing, power distribu- tion, and a translation path for the mobile base system tion, and a translation path for the mobile base system tion, and a translation path for the mobile base system (MBS). Major P3 subsystems include the segment-to- (MBS). Major P3 subsystems include the segment-to- (MBS). Major P3 subsystems include the segment-to- segment attach system (SSAS), solar alpha rotary joint segment attach system (SSAS), solar alpha rotary joint segment attach system (SSAS), solar alpha rotary joint (SARJ), and unpressurized cargo carrier attach system (SARJ), and unpressurized cargo carrier attach system (SARJ), and unpressurized cargo carrier attach system (UCCAS). Major P4 subsystems include the photovoltaic (UCCAS). Major P4 subsystems include the photovoltaic (UCCAS). Major P4 subsystems include the photovoltaic radiator (PVR), alpha joint interface structure (AJIS), modi- radiator (PVR), alpha joint interface structure (AJIS), modi- radiator (PVR), alpha joint interface structure (AJIS), modi- fied Rocketdyne truss attachment system (MRTAS), and fied Rocketdyne truss attachment system (MRTAS), and fied Rocketdyne truss attachment system (MRTAS), and integrated equipment assembly (IEA). integrated equipment assembly (IEA). integrated equipment assembly (IEA).

P3/P4 truss being installed during space shuttle mission P3/P4 truss being installed during space shuttle mission P3/P4 truss being installed during space shuttle mission STS-115/ISS-12A STS-115/ISS-12A STS-115/ISS-12A

Length: 44 ft, 10 in. (13.7 m) Length: 44 ft, 10 in. (13.7 m) Length: 44 ft, 10 in. (13.7 m) Width: 16 ft, 4 in. (5 m) Width: 16 ft, 4 in. (5 m) Width: 16 ft, 4 in. (5 m) Weight: 34,700 lb (15,740 kg) Weight: 34,700 lb (15,740 kg) Weight: 34,700 lb (15,740 kg)

B-32 B-32 B-32 With the P4 element, NASA has deployed the first exter- With the P4 element, NASA has deployed the first exter- With the P4 element, NASA has deployed the first exter- nal wireless instrumentation system (EWIS). The system nal wireless instrumentation system (EWIS). The system nal wireless instrumentation system (EWIS). The system consists of accelerometers placed around the outboard consists of accelerometers placed around the outboard consists of accelerometers placed around the outboard integrated truss structure. The vibration data seen by the integrated truss structure. The vibration data seen by the integrated truss structure. The vibration data seen by the accelerometers will be compared with their loads models accelerometers will be compared with their loads models accelerometers will be compared with their loads models so they can be further refined by engineers with actual on- so they can be further refined by engineers with actual on- so they can be further refined by engineers with actual on- orbit data to better predict the fatigue life and durability of orbit data to better predict the fatigue life and durability of orbit data to better predict the fatigue life and durability of the station’s integrated truss structure. This wireless sys- the station’s integrated truss structure. This wireless sys- the station’s integrated truss structure. This wireless sys- tem supplements 33 hard-wired accelerometers installed tem supplements 33 hard-wired accelerometers installed tem supplements 33 hard-wired accelerometers installed on the inboard truss elements (S0, S1, S3, P1, and P3). on the inboard truss elements (S0, S1, S3, P1, and P3). on the inboard truss elements (S0, S1, S3, P1, and P3). Starboard 5 (S5) Truss Starboard 5 (S5) Truss Starboard 5 (S5) Truss

During STS-118, space shuttle Endeavour delivered the During STS-118, space shuttle Endeavour delivered the During STS-118, space shuttle Endeavour delivered the Boeing-built square-shaped starboard 5 (S5) segment to Boeing-built square-shaped starboard 5 (S5) segment to Boeing-built square-shaped starboard 5 (S5) segment to the right side of the ISS. S5 is part of the 11-segment ITS the right side of the ISS. S5 is part of the 11-segment ITS the right side of the ISS. S5 is part of the 11-segment ITS and the third starboard truss element to be delivered. The and the third starboard truss element to be delivered. The and the third starboard truss element to be delivered. The ITS forms the station’s backbone with mountings for un- ITS forms the station’s backbone with mountings for un- ITS forms the station’s backbone with mountings for un- pressurized logistics carriers, radiators, solar arrays, and pressurized logistics carriers, radiators, solar arrays, and pressurized logistics carriers, radiators, solar arrays, and various other elements. S5 was attached to the S4 truss various other elements. S5 was attached to the S4 truss various other elements. S5 was attached to the S4 truss element via the Modified Rocketdyne Truss Attachment element via the Modified Rocketdyne Truss Attachment element via the Modified Rocketdyne Truss Attachment System (MRTAS) interface. S5 is used primarily to connect System (MRTAS) interface. S5 is used primarily to connect System (MRTAS) interface. S5 is used primarily to connect power, cooling lines, and serves as a spacer between the power, cooling lines, and serves as a spacer between the power, cooling lines, and serves as a spacer between the S4 photovoltaic module (PVM) and S6 PVM, which was S4 photovoltaic module (PVM) and S6 PVM, which was S4 photovoltaic module (PVM) and S6 PVM, which was joined during a later assembly mission. S5 is very similar joined during a later assembly mission. S5 is very similar joined during a later assembly mission. S5 is very similar in construction to the long spacer located on S6. Without in construction to the long spacer located on S6. Without in construction to the long spacer located on S6. Without the S5 short spacer, the S4 and S6 solar arrays would not the S5 short spacer, the S4 and S6 solar arrays would not the S5 short spacer, the S4 and S6 solar arrays would not be able to connect because of the way the photovoltaic be able to connect because of the way the photovoltaic be able to connect because of the way the photovoltaic arrays (PVAs) are deployed on orbit. arrays (PVAs) are deployed on orbit. arrays (PVAs) are deployed on orbit.

The girder-like structure is made of mostly aluminum and The girder-like structure is made of mostly aluminum and The girder-like structure is made of mostly aluminum and provides several extravehicular aids, robotic interfaces, provides several extravehicular aids, robotic interfaces, provides several extravehicular aids, robotic interfaces, ammonia servicing hardware (as part of the station’s Ex- ammonia servicing hardware (as part of the station’s Ex- ammonia servicing hardware (as part of the station’s Ex- ternal Active Thermal Control System that allows ammonia ternal Active Thermal Control System that allows ammonia ternal Active Thermal Control System that allows ammonia fluid to transfer from S4 to S6), and can also accommodate fluid to transfer from S4 to S6), and can also accommodate fluid to transfer from S4 to S6), and can also accommodate an external storage platform. The Enhanced Universal an external storage platform. The Enhanced Universal an external storage platform. The Enhanced Universal Trunnion Attachment System (EUTAS) allows platforms Trunnion Attachment System (EUTAS) allows platforms Trunnion Attachment System (EUTAS) allows platforms to be attached to S5 for the storage of additional science to be attached to S5 for the storage of additional science to be attached to S5 for the storage of additional science payloads or spare orbital replacement units (ORUs). S5 payloads or spare orbital replacement units (ORUs). S5 payloads or spare orbital replacement units (ORUs). S5 also has white thermal blankets on the structure, which also has white thermal blankets on the structure, which also has white thermal blankets on the structure, which help shade the S4 solar array assembly ORUs. help shade the S4 solar array assembly ORUs. help shade the S4 solar array assembly ORUs. Length: 11.1 ft (3.4 m) Length: 11.1 ft (3.4 m) Length: 11.1 ft (3.4 m) Width: 14.1 ft (4.3 m) Width: 14.1 ft (4.3 m) Width: 14.1 ft (4.3 m) Weight: 4,010 lb (1,819 kg) Weight: 4,010 lb (1,819 kg) Weight: 4,010 lb (1,819 kg)

B-33 B-33 B-33 Space shuttle Endeavour approaches the ISS during Space shuttle Endeavour approaches the ISS during Space shuttle Endeavour approaches the ISS during mission STS-118 with the S5 truss section ready to be mission STS-118 with the S5 truss section ready to be mission STS-118 with the S5 truss section ready to be installed. installed. installed.

Port 5 (P5) Truss Port 5 (P5) Truss Port 5 (P5) Truss The square-shaped port 5 (P5) truss segment delivered The square-shaped port 5 (P5) truss segment delivered The square-shaped port 5 (P5) truss segment delivered by STS-116 to the ISS is part of the 11-segment integrated by STS-116 to the ISS is part of the 11-segment integrated by STS-116 to the ISS is part of the 11-segment integrated truss structure and the sixth truss element to be delivered. truss structure and the sixth truss element to be delivered. truss structure and the sixth truss element to be delivered. The truss structure forms the backbone of the ISS with The truss structure forms the backbone of the ISS with The truss structure forms the backbone of the ISS with mountings for unpressurized logistics carriers, radiators, mountings for unpressurized logistics carriers, radiators, mountings for unpressurized logistics carriers, radiators, solar arrays, other hardware and the various elements. P5 solar arrays, other hardware and the various elements. P5 solar arrays, other hardware and the various elements. P5 was attached to the P4 truss element via the MRTAS inter- was attached to the P4 truss element via the MRTAS inter- was attached to the P4 truss element via the MRTAS inter- face. P5 is used primarily to connect power and cooling face. P5 is used primarily to connect power and cooling face. P5 is used primarily to connect power and cooling lines and serve as a spacer between the P4 photovoltaic lines and serve as a spacer between the P4 photovoltaic lines and serve as a spacer between the P4 photovoltaic module (PVM) and P6 PVM. P5 is very similar in construc- module (PVM) and P6 PVM. P5 is very similar in construc- module (PVM) and P6 PVM. P5 is very similar in construc- tion to the long spacer located on P6. Without the P5 short tion to the long spacer located on P6. Without the P5 short tion to the long spacer located on P6. Without the P5 short spacer, the P4 and P6 solar arrays would not be able to spacer, the P4 and P6 solar arrays would not be able to spacer, the P4 and P6 solar arrays would not be able to connect because of the way the photovoltaic arrays are connect because of the way the photovoltaic arrays are connect because of the way the photovoltaic arrays are deployed on orbit. deployed on orbit. deployed on orbit.

The new P5 truss awaits installation following the hand-off The new P5 truss awaits installation following the hand-off The new P5 truss awaits installation following the hand-off from the shuttle’s robotic arm to the station’s Canadarm2. from the shuttle’s robotic arm to the station’s Canadarm2. from the shuttle’s robotic arm to the station’s Canadarm2.

Length: 11 ft, 1 in. (3.37 m) Length: 11 ft, 1 in. (3.37 m) Length: 11 ft, 1 in. (3.37 m) Width: 14 ft, 11 in. (4.55 m) Width: 14 ft, 11 in. (4.55 m) Width: 14 ft, 11 in. (4.55 m) Weight: 4,107 lb (1,863 kg) Weight: 4,107 lb (1,863 kg) Weight: 4,107 lb (1,863 kg)

B-34 B-34 B-34 The girder-like structure is made of mostly aluminum and The girder-like structure is made of mostly aluminum and The girder-like structure is made of mostly aluminum and provides several extravehicular aids, robotic interfaces, provides several extravehicular aids, robotic interfaces, provides several extravehicular aids, robotic interfaces, ammonia servicing hardware (as part of the station’s Ex- ammonia servicing hardware (as part of the station’s Ex- ammonia servicing hardware (as part of the station’s Ex- ternal Active Thermal Control System that allows ammonia ternal Active Thermal Control System that allows ammonia ternal Active Thermal Control System that allows ammonia fluid to transfer from P4 to P6) and can also accommodate fluid to transfer from P4 to P6) and can also accommodate fluid to transfer from P4 to P6) and can also accommodate an external storage platform. The Enhanced Universal an external storage platform. The Enhanced Universal an external storage platform. The Enhanced Universal Trunnion Attachment System (EUTAS) allows platforms Trunnion Attachment System (EUTAS) allows platforms Trunnion Attachment System (EUTAS) allows platforms to be attached to P5 for the storage of additional science to be attached to P5 for the storage of additional science to be attached to P5 for the storage of additional science payloads or spare orbital replacement units. P5 also has payloads or spare orbital replacement units. P5 also has payloads or spare orbital replacement units. P5 also has white thermal blankets on the structure, which help shade white thermal blankets on the structure, which help shade white thermal blankets on the structure, which help shade the P4 solar array assembly ORUs. the P4 solar array assembly ORUs. the P4 solar array assembly ORUs. Another element of P5 is the photovoltaic radiator grapple Another element of P5 is the photovoltaic radiator grapple Another element of P5 is the photovoltaic radiator grapple feature (PVRGF). For launch, the PVRGF was stowed on feature (PVRGF). For launch, the PVRGF was stowed on feature (PVRGF). For launch, the PVRGF was stowed on top of P5 and used by the shuttle and station robotic arms top of P5 and used by the shuttle and station robotic arms top of P5 and used by the shuttle and station robotic arms to grab P5 to lift it from the shuttle cargo bay and attach to grab P5 to lift it from the shuttle cargo bay and attach to grab P5 to lift it from the shuttle cargo bay and attach it to the station. After P5 was attached to P4, the PVRGF it to the station. After P5 was attached to P4, the PVRGF it to the station. After P5 was attached to P4, the PVRGF was relocated to the truss' keel. P5 also contains a remote was relocated to the truss' keel. P5 also contains a remote was relocated to the truss' keel. P5 also contains a remote sensor box, two tri-axial accelerators and two antenna as- sensor box, two tri-axial accelerators and two antenna as- sensor box, two tri-axial accelerators and two antenna as- semblies as part of the External Wireless Instrumentation semblies as part of the External Wireless Instrumentation semblies as part of the External Wireless Instrumentation System (EWIS). EWIS will give engineers a better under- System (EWIS). EWIS will give engineers a better under- System (EWIS). EWIS will give engineers a better under- standing of the actual response of the truss system on orbit standing of the actual response of the truss system on orbit standing of the actual response of the truss system on orbit to vibration and other stresses and help engineers predict to vibration and other stresses and help engineers predict to vibration and other stresses and help engineers predict the fatigue life and durability of the truss structure. the fatigue life and durability of the truss structure. the fatigue life and durability of the truss structure. Boeing’s Rocketdyne Power and Propulsion division (now Boeing’s Rocketdyne Power and Propulsion division (now Boeing’s Rocketdyne Power and Propulsion division (now Hamilton Sundstrand) designed P5. The component Hamilton Sundstrand) designed P5. The component Hamilton Sundstrand) designed P5. The component was constructed in Tulsa, Okla., and arrived at Kennedy was constructed in Tulsa, Okla., and arrived at Kennedy was constructed in Tulsa, Okla., and arrived at Kennedy Space Center in 2001 for final manufacture, acceptance Space Center in 2001 for final manufacture, acceptance Space Center in 2001 for final manufacture, acceptance and checkout. Boeing will continue to provide sustaining and checkout. Boeing will continue to provide sustaining and checkout. Boeing will continue to provide sustaining engineering of P5 and for the entire integrated truss engineering of P5 and for the entire integrated truss engineering of P5 and for the entire integrated truss assembly. assembly. assembly. Starboard 6 (S6) Truss Starboard 6 (S6) Truss Starboard 6 (S6) Truss The Boeing-designed starboard 6 (S6), the final truss The Boeing-designed starboard 6 (S6), the final truss The Boeing-designed starboard 6 (S6), the final truss element delivered by space shuttle Discovery on mission element delivered by space shuttle Discovery on mission element delivered by space shuttle Discovery on mission STS-119/ISS-15A, completed the station’s 11-segment STS-119/ISS-15A, completed the station’s 11-segment STS-119/ISS-15A, completed the station’s 11-segment integrated truss structure (ITS). The 310-foot ITS to which integrated truss structure (ITS). The 310-foot ITS to which integrated truss structure (ITS). The 310-foot ITS to which the S6 is attached forms the backbone of the space sta- the S6 is attached forms the backbone of the space sta- the S6 is attached forms the backbone of the space sta- tion, with mountings for unpressurized logistics carriers, tion, with mountings for unpressurized logistics carriers, tion, with mountings for unpressurized logistics carriers, radiators, solar arrays, and various elements. radiators, solar arrays, and various elements. radiators, solar arrays, and various elements.

B-35 B-35 B-35 Backdropped by the blackness of space and Earth’s Backdropped by the blackness of space and Earth’s Backdropped by the blackness of space and Earth’s horizon, a portion of the Columbus laboratory, starboard horizon, a portion of the Columbus laboratory, starboard horizon, a portion of the Columbus laboratory, starboard truss, and solar array panels are shown after the installa- truss, and solar array panels are shown after the installa- truss, and solar array panels are shown after the installa- tion of the S6 truss during space shuttle mission STS-119/ tion of the S6 truss during space shuttle mission STS-119/ tion of the S6 truss during space shuttle mission STS-119/ ISS-15A. ISS-15A. ISS-15A.

Major subsystems of the S6 truss are the starboard out- Major subsystems of the S6 truss are the starboard out- Major subsystems of the S6 truss are the starboard out- board photovoltaic module (PVM), the photovoltaic radia- board photovoltaic module (PVM), the photovoltaic radia- board photovoltaic module (PVM), the photovoltaic radia- tor (PVR), the long spacer truss (LST), and the modified tor (PVR), the long spacer truss (LST), and the modified tor (PVR), the long spacer truss (LST), and the modified Rocketdyne truss attachment system (MRTAS). Rocketdyne truss attachment system (MRTAS). Rocketdyne truss attachment system (MRTAS). The PVMs use a large number of solar cells assembled The PVMs use a large number of solar cells assembled The PVMs use a large number of solar cells assembled onto solar arrays to produce high power levels. NASA onto solar arrays to produce high power levels. NASA onto solar arrays to produce high power levels. NASA and Lockheed Martin developed a method of mounting and Lockheed Martin developed a method of mounting and Lockheed Martin developed a method of mounting the solar arrays on a “blanket” that can be folded like an the solar arrays on a “blanket” that can be folded like an the solar arrays on a “blanket” that can be folded like an accordion for delivery to space and then deployed to its accordion for delivery to space and then deployed to its accordion for delivery to space and then deployed to its full size once in orbit. full size once in orbit. full size once in orbit. The station power system, consisting of U.S. and Russian The station power system, consisting of U.S. and Russian The station power system, consisting of U.S. and Russian hardware and four photovoltaic modules, uses between hardware and four photovoltaic modules, uses between hardware and four photovoltaic modules, uses between 84–120 kilowatts of power. Some of the electricity is 84–120 kilowatts of power. Some of the electricity is 84–120 kilowatts of power. Some of the electricity is needed to operate space station systems, but the addition needed to operate space station systems, but the addition needed to operate space station systems, but the addition of the S6 nearly doubles the amount of power available of the S6 nearly doubles the amount of power available of the S6 nearly doubles the amount of power available to perform scientific experiments on the station, from 15 to perform scientific experiments on the station, from 15 to perform scientific experiments on the station, from 15 kilowatts to 30 kilowatts. kilowatts to 30 kilowatts. kilowatts to 30 kilowatts. The two solar array wings (SAWs) on the S6 module were The two solar array wings (SAWs) on the S6 module were The two solar array wings (SAWs) on the S6 module were deployed in the opposite direction of the other. Each SAW deployed in the opposite direction of the other. Each SAW deployed in the opposite direction of the other. Each SAW is made up of two solar blankets mounted to a common is made up of two solar blankets mounted to a common is made up of two solar blankets mounted to a common mast. The addition of S6 brings the station’s total SAWs mast. The addition of S6 brings the station’s total SAWs mast. The addition of S6 brings the station’s total SAWs to eight. Each wing is 115 by 38 feet wide and, with all to eight. Each wing is 115 by 38 feet wide and, with all to eight. Each wing is 115 by 38 feet wide and, with all eight fully deployed, has a total surface area of 38,400 eight fully deployed, has a total surface area of 38,400 eight fully deployed, has a total surface area of 38,400 square feet. square feet. square feet. Length: 45.4 ft (13.8 m) Length: 45.4 ft (13.8 m) Length: 45.4 ft (13.8 m) Width: 16.3 ft (5 m) Width: 16.3 ft (5 m) Width: 16.3 ft (5 m) Weight: 30,937 lb (14,033 kg) Weight: 30,937 lb (14,033 kg) Weight: 30,937 lb (14,033 kg)

B-36 B-36 B-36 The solar arrays produce more power than can be made The solar arrays produce more power than can be made The solar arrays produce more power than can be made available to the station’s systems and experiments. Be- available to the station’s systems and experiments. Be- available to the station’s systems and experiments. Be- cause all or part of the solar arrays are eclipsed by the cause all or part of the solar arrays are eclipsed by the cause all or part of the solar arrays are eclipsed by the Earth or station structure at times, batteries are used to Earth or station structure at times, batteries are used to Earth or station structure at times, batteries are used to store electricity for use during those periods. store electricity for use during those periods. store electricity for use during those periods.

A unique feature of the S6 is that it carries two spare battery A unique feature of the S6 is that it carries two spare battery A unique feature of the S6 is that it carries two spare battery charge/discharge units (BCDUs), used for controlling the charge/discharge units (BCDUs), used for controlling the charge/discharge units (BCDUs), used for controlling the charge and discharge of spare batteries on the station. The charge and discharge of spare batteries on the station. The charge and discharge of spare batteries on the station. The S6 segment was modified to carry the additional BCDUs, S6 segment was modified to carry the additional BCDUs, S6 segment was modified to carry the additional BCDUs, attached to the segment’s long spacer truss structure. attached to the segment’s long spacer truss structure. attached to the segment’s long spacer truss structure.

The SAWs also are oriented by the beta gimbal assem- The SAWs also are oriented by the beta gimbal assem- The SAWs also are oriented by the beta gimbal assem- bly (BGA), which can change the pitch of the wings by bly (BGA), which can change the pitch of the wings by bly (BGA), which can change the pitch of the wings by spinning the solar array. Both the solar alpha rotary joint spinning the solar array. Both the solar alpha rotary joint spinning the solar array. Both the solar alpha rotary joint (SARJ) and BGA are pointing mechanisms and mechani- (SARJ) and BGA are pointing mechanisms and mechani- (SARJ) and BGA are pointing mechanisms and mechani- cal devices used to point the arrays toward the sun. They cal devices used to point the arrays toward the sun. They cal devices used to point the arrays toward the sun. They can follow an angle target and rotate to that target in the can follow an angle target and rotate to that target in the can follow an angle target and rotate to that target in the direction toward the sun. Controllers in orbit continuously direction toward the sun. Controllers in orbit continuously direction toward the sun. Controllers in orbit continuously update those targets so they keep moving as the station update those targets so they keep moving as the station update those targets so they keep moving as the station orbits the Earth every 90 minutes, maintaining the same orbits the Earth every 90 minutes, maintaining the same orbits the Earth every 90 minutes, maintaining the same orientation toward the sun at the same orbital rate. The orientation toward the sun at the same orbital rate. The orientation toward the sun at the same orbital rate. The SARJ mechanism rotates 360 degrees every orbit, or about SARJ mechanism rotates 360 degrees every orbit, or about SARJ mechanism rotates 360 degrees every orbit, or about 4 degrees per minute, whereas the BGA moves only about 4 degrees per minute, whereas the BGA moves only about 4 degrees per minute, whereas the BGA moves only about four or five degrees per day. four or five degrees per day. four or five degrees per day.

Port 6 (P6) Truss—Solar Array Port 6 (P6) Truss—Solar Array Port 6 (P6) Truss—Solar Array

The U.S.-made photovoltaic solar arrays attached to the The U.S.-made photovoltaic solar arrays attached to the The U.S.-made photovoltaic solar arrays attached to the port 6 (P6) truss segment use purified silicon solar cells port 6 (P6) truss segment use purified silicon solar cells port 6 (P6) truss segment use purified silicon solar cells to directly convert light to electricity, which allows the crew to directly convert light to electricity, which allows the crew to directly convert light to electricity, which allows the crew to live comfortably, to safely operate the station, and to to live comfortably, to safely operate the station, and to to live comfortably, to safely operate the station, and to perform scientific experiments. perform scientific experiments. perform scientific experiments.

ISS after installation of the P6 truss on space shuttle mis- ISS after installation of the P6 truss on space shuttle mis- ISS after installation of the P6 truss on space shuttle mis- sion STS-97/ISS-4A sion STS-97/ISS-4A sion STS-97/ISS-4A

Length: 240 ft (73.2 m) Length: 240 ft (73.2 m) Length: 240 ft (73.2 m) Width: 35 ft (10.7 m) Width: 35 ft (10.7 m) Width: 35 ft (10.7 m) Weight: 30,689 lb (13,920 kg) Weight: 30,689 lb (13,920 kg) Weight: 30,689 lb (13,920 kg)

B-37 B-37 B-37 External Stowage Platforms External Stowage Platforms External Stowage Platforms The External Stowage Platforms (ESPs) are unpressurized The External Stowage Platforms (ESPs) are unpressurized The External Stowage Platforms (ESPs) are unpressurized external storage pallets with attachment sites capable of external storage pallets with attachment sites capable of external storage pallets with attachment sites capable of holding ISS spare parts and assemblies. The pallets also holding ISS spare parts and assemblies. The pallets also holding ISS spare parts and assemblies. The pallets also have handrails and attachment points for tethers and foot have handrails and attachment points for tethers and foot have handrails and attachment points for tethers and foot restraints that astronauts can use while working with orbital restraints that astronauts can use while working with orbital restraints that astronauts can use while working with orbital replacement units (ORUs), which are attached to the ESPs replacement units (ORUs), which are attached to the ESPs replacement units (ORUs), which are attached to the ESPs with Flight Releasable Attachment Mechanisms (FRAMs). with Flight Releasable Attachment Mechanisms (FRAMs). with Flight Releasable Attachment Mechanisms (FRAMs). The ISS robotic arm can be used to move large ORUs The ISS robotic arm can be used to move large ORUs The ISS robotic arm can be used to move large ORUs stored on the pallet, but astronauts can move smaller parts stored on the pallet, but astronauts can move smaller parts stored on the pallet, but astronauts can move smaller parts during a spacewalk. Electrical power for the pallets and during a spacewalk. Electrical power for the pallets and during a spacewalk. Electrical power for the pallets and their contents is provided by the ISS. Most of the ORUs their contents is provided by the ISS. Most of the ORUs their contents is provided by the ISS. Most of the ORUs have heaters to keep their internal components from get- have heaters to keep their internal components from get- have heaters to keep their internal components from get- ting too cold while being stored on an ESP. ting too cold while being stored on an ESP. ting too cold while being stored on an ESP. ESP-1 was installed during STS-102/ISS-5A.1 and is ESP-1 was installed during STS-102/ISS-5A.1 and is ESP-1 was installed during STS-102/ISS-5A.1 and is mounted on the aft portion of Destiny. ESP-1 is the smallest mounted on the aft portion of Destiny. ESP-1 is the smallest mounted on the aft portion of Destiny. ESP-1 is the smallest ESP and has two FRAMs to store ORUs. Unity provides ESP and has two FRAMs to store ORUs. Unity provides ESP and has two FRAMs to store ORUs. Unity provides power to ESP-1, which in turn makes power available to power to ESP-1, which in turn makes power available to power to ESP-1, which in turn makes power available to both ORU storage areas. both ORU storage areas. both ORU storage areas. ESP-2, installed during STS-114/ISS-LF1, is derived from ESP-2, installed during STS-114/ISS-LF1, is derived from ESP-2, installed during STS-114/ISS-LF1, is derived from an Integrated Cargo Carrier (ICC), an equipment carrier an Integrated Cargo Carrier (ICC), an equipment carrier an Integrated Cargo Carrier (ICC), an equipment carrier designed for use in the payload of the orbiter. ESP-2, the designed for use in the payload of the orbiter. ESP-2, the designed for use in the payload of the orbiter. ESP-2, the largest of the ESPs with eight FRAMs, was adapted for de- largest of the ESPs with eight FRAMs, was adapted for de- largest of the ESPs with eight FRAMs, was adapted for de- ployment on the ISS by developing a device to attach it to ployment on the ISS by developing a device to attach it to ployment on the ISS by developing a device to attach it to the ISS Quest airlock. Primary power for ESP-2 comes from the ISS Quest airlock. Primary power for ESP-2 comes from the ISS Quest airlock. Primary power for ESP-2 comes from Unity, and secondary power comes from the S0 truss. Unity, and secondary power comes from the S0 truss. Unity, and secondary power comes from the S0 truss. ESP-3, installed during STS-118/ISS-13A.1, was the first ESP-3, installed during STS-118/ISS-13A.1, was the first ESP-3, installed during STS-118/ISS-13A.1, was the first ISS element installed completely by robotics using only ISS element installed completely by robotics using only ISS element installed completely by robotics using only the shuttle and station’s robotic arms, an External Berth- the shuttle and station’s robotic arms, an External Berth- the shuttle and station’s robotic arms, an External Berth- ing Camera System (BCS), and a Photovoltaic Radiator ing Camera System (BCS), and a Photovoltaic Radiator ing Camera System (BCS), and a Photovoltaic Radiator Grapple Fixture (PVRGF). ESP-3 has six FRAMs to secure Grapple Fixture (PVRGF). ESP-3 has six FRAMs to secure Grapple Fixture (PVRGF). ESP-3 has six FRAMs to secure or release the ORUs and other equipment stored on it and or release the ORUs and other equipment stored on it and or release the ORUs and other equipment stored on it and Ammonia Tank Assembly (ATA) Flight Support Equipment Ammonia Tank Assembly (ATA) Flight Support Equipment Ammonia Tank Assembly (ATA) Flight Support Equipment (FSE) directly mounted to a seventh site. Like ESP-2, the (FSE) directly mounted to a seventh site. Like ESP-2, the (FSE) directly mounted to a seventh site. Like ESP-2, the platform is derived from an ICC, and it is attached to the platform is derived from an ICC, and it is attached to the platform is derived from an ICC, and it is attached to the P3 truss, which supplies its primary power. P3 truss, which supplies its primary power. P3 truss, which supplies its primary power.

The space shuttle robotic arm moves away following the The space shuttle robotic arm moves away following the The space shuttle robotic arm moves away following the hand-off of ESP-3 to the station’s robotic arm while docked hand-off of ESP-3 to the station’s robotic arm while docked hand-off of ESP-3 to the station’s robotic arm while docked with the ISS during mission STS-118/ISS-13A.1. with the ISS during mission STS-118/ISS-13A.1. with the ISS during mission STS-118/ISS-13A.1.

B-38 B-38 B-38 ExPRESS Logistics Carrier ExPRESS Logistics Carrier ExPRESS Logistics Carrier The Expedite the Processing of Experiments to the The Expedite the Processing of Experiments to the The Expedite the Processing of Experiments to the Space Station (ExPRESS) Logistics Carrier (ELC) is an Space Station (ExPRESS) Logistics Carrier (ELC) is an Space Station (ExPRESS) Logistics Carrier (ELC) is an unpressurized attached payload platform for the ISS that unpressurized attached payload platform for the ISS that unpressurized attached payload platform for the ISS that provides mechanical mounting surfaces, electrical power, provides mechanical mounting surfaces, electrical power, provides mechanical mounting surfaces, electrical power, and command and data handling services for science and command and data handling services for science and command and data handling services for science experiments. ELC was formerly called "ExPRESS Pallet" experiments. ELC was formerly called "ExPRESS Pallet" experiments. ELC was formerly called "ExPRESS Pallet" and is the unpressurized counterpart to the pressurized and is the unpressurized counterpart to the pressurized and is the unpressurized counterpart to the pressurized ExPRESS Rack. ExPRESS Rack. ExPRESS Rack. An ELC provides scientists with a platform and infrastruc- An ELC provides scientists with a platform and infrastruc- An ELC provides scientists with a platform and infrastruc- ture to deploy experiments in the vacuum of space without ture to deploy experiments in the vacuum of space without ture to deploy experiments in the vacuum of space without requiring a separate dedicated Earth-orbiting satellite. ELCs requiring a separate dedicated Earth-orbiting satellite. ELCs requiring a separate dedicated Earth-orbiting satellite. ELCs interface directly with the ISS integrated truss carrier attach interface directly with the ISS integrated truss carrier attach interface directly with the ISS integrated truss carrier attach system (CAS). The ELC serves as a parking place for spare system (CAS). The ELC serves as a parking place for spare system (CAS). The ELC serves as a parking place for spare hardware that can be replaced robotically once on orbit. hardware that can be replaced robotically once on orbit. hardware that can be replaced robotically once on orbit. Five ELC units are planned, with all having full-up avionics Five ELC units are planned, with all having full-up avionics Five ELC units are planned, with all having full-up avionics subsystems. Four ELCs will be delivered to the ISS before subsystems. Four ELCs will be delivered to the ISS before subsystems. Four ELCs will be delivered to the ISS before the scheduled retirement of the space shuttle. Two ELCs the scheduled retirement of the space shuttle. Two ELCs the scheduled retirement of the space shuttle. Two ELCs will be attached to the starboard truss 3 (S3), and two will be attached to the starboard truss 3 (S3), and two will be attached to the starboard truss 3 (S3), and two ELCs will be attached to the port truss 3 (P3). By attach- ELCs will be attached to the port truss 3 (P3). By attach- ELCs will be attached to the port truss 3 (P3). By attach- ing the ELCs at the S3/P3 sites, a variety of views such as ing the ELCs at the S3/P3 sites, a variety of views such as ing the ELCs at the S3/P3 sites, a variety of views such as zenith (deep space) or nadir (Earthward) direction with a zenith (deep space) or nadir (Earthward) direction with a zenith (deep space) or nadir (Earthward) direction with a combination of ram (forward) or wake (aft) pointing allows combination of ram (forward) or wake (aft) pointing allows combination of ram (forward) or wake (aft) pointing allows for many possible viewing opportunities. for many possible viewing opportunities. for many possible viewing opportunities.

Each ELC can accommodate 12 flight releasable attach- Each ELC can accommodate 12 flight releasable attach- Each ELC can accommodate 12 flight releasable attach- ment mechanism (FRAM)-based cargos, which include ment mechanism (FRAM)-based cargos, which include ment mechanism (FRAM)-based cargos, which include two payload attached sites. The mass capacity for an ELC two payload attached sites. The mass capacity for an ELC two payload attached sites. The mass capacity for an ELC is 9,800 lb (4,445 kg) with a volume of 98 ft3 (30 m3). The is 9,800 lb (4,445 kg) with a volume of 98 ft3 (30 m3). The is 9,800 lb (4,445 kg) with a volume of 98 ft3 (30 m3). The ISS provides power to the ELCs through two 3 kW, 120 Vdc ISS provides power to the ELCs through two 3 kW, 120 Vdc ISS provides power to the ELCs through two 3 kW, 120 Vdc feeds at the ISS-to-ELC interface. The ELC power distribu- feeds at the ISS-to-ELC interface. The ELC power distribu- feeds at the ISS-to-ELC interface. The ELC power distribu- tion module converts the 120 Vdc power to 120 Vdc and tion module converts the 120 Vdc power to 120 Vdc and tion module converts the 120 Vdc power to 120 Vdc and 28 Vdc. Both power voltages are provided to each payload 28 Vdc. Both power voltages are provided to each payload 28 Vdc. Both power voltages are provided to each payload attached site by separated buses. attached site by separated buses. attached site by separated buses.

Within the electrical subsystem of the ELC, the ExPRESS Within the electrical subsystem of the ELC, the ExPRESS Within the electrical subsystem of the ELC, the ExPRESS carrier avionics (ExPCA) provide electrical power distribu- carrier avionics (ExPCA) provide electrical power distribu- carrier avionics (ExPCA) provide electrical power distribu- tion to experiments and data interfaces to the ISS. Within tion to experiments and data interfaces to the ISS. Within tion to experiments and data interfaces to the ISS. Within the ExPCA, the ColdFire-based flight computer, software, the ExPCA, the ColdFire-based flight computer, software, the ExPCA, the ColdFire-based flight computer, software, and related electronics comprise its "flight controller unit" and related electronics comprise its "flight controller unit" and related electronics comprise its "flight controller unit" (FCU). (FCU). (FCU).

STS-129/ISS-ULF3 marked the first flight of ELC1 and STS-129/ISS-ULF3 marked the first flight of ELC1 and STS-129/ISS-ULF3 marked the first flight of ELC1 and ELC2. ELC1 was mounted on the P3 truss element CAS, ELC2. ELC1 was mounted on the P3 truss element CAS, ELC2. ELC1 was mounted on the P3 truss element CAS, while ELC2 was placed on the S3 truss upper outboard while ELC2 was placed on the S3 truss upper outboard while ELC2 was placed on the S3 truss upper outboard passive attachment system (PAS). The CAS and PAS were passive attachment system (PAS). The CAS and PAS were passive attachment system (PAS). The CAS and PAS were deployed during the STS-128 mission. deployed during the STS-128 mission. deployed during the STS-128 mission.

B-39 B-39 B-39 Canadarm2 mated ELC2 to the PAS on the ISS S3 truss, Canadarm2 mated ELC2 to the PAS on the ISS S3 truss, Canadarm2 mated ELC2 to the PAS on the ISS S3 truss, controlled by space shuttle and station crews during controlled by space shuttle and station crews during controlled by space shuttle and station crews during space shuttle mission STS-129. space shuttle mission STS-129. space shuttle mission STS-129.

Both ELC1 and ELC2 measure approximately 16 ft by Both ELC1 and ELC2 measure approximately 16 ft by Both ELC1 and ELC2 measure approximately 16 ft by 14 ft (5 m by 4.3 m without the orbital replacement units 14 ft (5 m by 4.3 m without the orbital replacement units 14 ft (5 m by 4.3 m without the orbital replacement units installed) and weigh about 3,500 lb (1,588 kg without the installed) and weigh about 3,500 lb (1,588 kg without the installed) and weigh about 3,500 lb (1,588 kg without the ORUs).The weight of ELC1 with ORUs was approximately ORUs).The weight of ELC1 with ORUs was approximately ORUs).The weight of ELC1 with ORUs was approximately 13,850 lb (6,282 kg) while ELC2 weighed 13,400 lb (6,078 13,850 lb (6,282 kg) while ELC2 weighed 13,400 lb (6,078 13,850 lb (6,282 kg) while ELC2 weighed 13,400 lb (6,078 kg) with ORUs installed. kg) with ORUs installed. kg) with ORUs installed. A total of 14 large ORUs were carried on ELC1 and ELC2. A total of 14 large ORUs were carried on ELC1 and ELC2. A total of 14 large ORUs were carried on ELC1 and ELC2. All of the hardware for this mission was processed by All of the hardware for this mission was processed by All of the hardware for this mission was processed by Boeing under its Checkout, Assembly and Payload Boeing under its Checkout, Assembly and Payload Boeing under its Checkout, Assembly and Payload Processing Services (CAPPS) contract with NASA. The Processing Services (CAPPS) contract with NASA. The Processing Services (CAPPS) contract with NASA. The ORUs included the ammonia tank assembly (ATA), bat- ORUs included the ammonia tank assembly (ATA), bat- ORUs included the ammonia tank assembly (ATA), bat- tery charger discharge unit (BCDU), cargo transportation tery charger discharge unit (BCDU), cargo transportation tery charger discharge unit (BCDU), cargo transportation container (CTC), two control moment gyroscopes (CMGs), container (CTC), two control moment gyroscopes (CMGs), container (CTC), two control moment gyroscopes (CMGs), high-pressure gas tank (HPGT), Canadarm2 latching high-pressure gas tank (HPGT), Canadarm2 latching high-pressure gas tank (HPGT), Canadarm2 latching end effector (LEE), Materials International Space Station end effector (LEE), Materials International Space Station end effector (LEE), Materials International Space Station Experiment 7 (MISSE-7), two nitrogen tank assemblies Experiment 7 (MISSE-7), two nitrogen tank assemblies Experiment 7 (MISSE-7), two nitrogen tank assemblies (NTAs), plasma contactor unit (PCU), two pump module (NTAs), plasma contactor unit (PCU), two pump module (NTAs), plasma contactor unit (PCU), two pump module assemblies (PMAs), and a trailing umbilical system–reel assemblies (PMAs), and a trailing umbilical system–reel assemblies (PMAs), and a trailing umbilical system–reel assembly (TUS-RA). assembly (TUS-RA). assembly (TUS-RA). ELC4 is currently slated for mission STS-134, scheduled ELC4 is currently slated for mission STS-134, scheduled ELC4 is currently slated for mission STS-134, scheduled to launch in July 2010. ELC3 is currently slated for mis- to launch in July 2010. ELC3 is currently slated for mis- to launch in July 2010. ELC3 is currently slated for mis- sion STS-133, launching in September 2010. ELC5 is not sion STS-133, launching in September 2010. ELC5 is not sion STS-133, launching in September 2010. ELC5 is not manifested and is considered a flight spare. The Alpha manifested and is considered a flight spare. The Alpha manifested and is considered a flight spare. The Alpha Magnetic Spectrometer (AMS) will occupy the spot of Magnetic Spectrometer (AMS) will occupy the spot of Magnetic Spectrometer (AMS) will occupy the spot of ELC5 on the truss. ELC5 on the truss. ELC5 on the truss. Engineers from NASA’s Goddard Space Flight Center Engineers from NASA’s Goddard Space Flight Center Engineers from NASA’s Goddard Space Flight Center (GSFC) in Greenbelt, Md., developed the lightweight ELC (GSFC) in Greenbelt, Md., developed the lightweight ELC (GSFC) in Greenbelt, Md., developed the lightweight ELC design, which incorporates elements of both the ExPRESS design, which incorporates elements of both the ExPRESS design, which incorporates elements of both the ExPRESS Pallet and the unpressurized logistics carrier. Remmele Pallet and the unpressurized logistics carrier. Remmele Pallet and the unpressurized logistics carrier. Remmele Engineering, based in Minneapolis, Minn., built the inte- Engineering, based in Minneapolis, Minn., built the inte- Engineering, based in Minneapolis, Minn., built the inte- gral aluminum ELC decks for NASA. GSFC, with support gral aluminum ELC decks for NASA. GSFC, with support gral aluminum ELC decks for NASA. GSFC, with support from JSC and MSFC, served as the overall integrator and from JSC and MSFC, served as the overall integrator and from JSC and MSFC, served as the overall integrator and manufacturer for ELC1 and ELC2. manufacturer for ELC1 and ELC2. manufacturer for ELC1 and ELC2.

B-40 B-40 B-40 Multipurpose Logistics Modules (MPLMs) Multipurpose Logistics Modules (MPLMs) Multipurpose Logistics Modules (MPLMs)

The MPLM was originally designed for Space Station The MPLM was originally designed for Space Station The MPLM was originally designed for Space Station Freedom, the precursor design to the ISS. Initially, it was Freedom, the precursor design to the ISS. Initially, it was Freedom, the precursor design to the ISS. Initially, it was to be built by Boeing, but in 1992 the Italian Space Agency to be built by Boeing, but in 1992 the Italian Space Agency to be built by Boeing, but in 1992 the Italian Space Agency (ASI) announced that it would build a "Mini-Pressurized (ASI) announced that it would build a "Mini-Pressurized (ASI) announced that it would build a "Mini-Pressurized Logistics Module" able to carry approximately 9,000 lb of Logistics Module" able to carry approximately 9,000 lb of Logistics Module" able to carry approximately 9,000 lb of cargo. After a 1993 redesign, the length was doubled, and cargo. After a 1993 redesign, the length was doubled, and cargo. After a 1993 redesign, the length was doubled, and it was renamed the "Multi-Purpose Logistics Module." it was renamed the "Multi-Purpose Logistics Module." it was renamed the "Multi-Purpose Logistics Module."

The MPLMs were Italy's contribution to the ISS, and in The MPLMs were Italy's contribution to the ISS, and in The MPLMs were Italy's contribution to the ISS, and in exchange, the Italian Space Agency was given access to exchange, the Italian Space Agency was given access to exchange, the Italian Space Agency was given access to research time on the station. ASI chose the names Leon- research time on the station. ASI chose the names Leon- research time on the station. ASI chose the names Leon- ardo, Raffaello, and Donatello for the modules because ardo, Raffaello, and Donatello for the modules because ardo, Raffaello, and Donatello for the modules because they represent some of the great engineers in Italian his- they represent some of the great engineers in Italian his- they represent some of the great engineers in Italian his- tory: Leonardo da Vinci, Donato di Niccolo di Betto Bardi, tory: Leonardo da Vinci, Donato di Niccolo di Betto Bardi, tory: Leonardo da Vinci, Donato di Niccolo di Betto Bardi, and Raffaello Sanzio. and Raffaello Sanzio. and Raffaello Sanzio.

The pressurized, reusable MPLMs function both as ISS The pressurized, reusable MPLMs function both as ISS The pressurized, reusable MPLMs function both as ISS "moving van" cargo carriers and as a space station mod- "moving van" cargo carriers and as a space station mod- "moving van" cargo carriers and as a space station mod- ule. Each MPLM is sent to the ISS via the space shuttle. ule. Each MPLM is sent to the ISS via the space shuttle. ule. Each MPLM is sent to the ISS via the space shuttle. When in the cargo bay, the MPLM is independent of the When in the cargo bay, the MPLM is independent of the When in the cargo bay, the MPLM is independent of the shuttle cabin, and there is no passageway for crew mem- shuttle cabin, and there is no passageway for crew mem- shuttle cabin, and there is no passageway for crew mem- bers to travel from the shuttle cabin to the module. After bers to travel from the shuttle cabin to the module. After bers to travel from the shuttle cabin to the module. After the shuttle docks with the ISS, the shuttle's robotic arm lifts the shuttle docks with the ISS, the shuttle's robotic arm lifts the shuttle docks with the ISS, the shuttle's robotic arm lifts and transfers the MPLM from the cargo bay to the station. and transfers the MPLM from the cargo bay to the station. and transfers the MPLM from the cargo bay to the station. It's then bolted in place to the Node 2 Harmony module It's then bolted in place to the Node 2 Harmony module It's then bolted in place to the Node 2 Harmony module nadir port, and power, data, and water cables make it a nadir port, and power, data, and water cables make it a nadir port, and power, data, and water cables make it a fully functioning extra work area. fully functioning extra work area. fully functioning extra work area.

ISS crew member Yuri Gidzenko is surrounded by transient ISS crew member Yuri Gidzenko is surrounded by transient ISS crew member Yuri Gidzenko is surrounded by transient hardware aboard MPLM Leonardo, which was carried to hardware aboard MPLM Leonardo, which was carried to hardware aboard MPLM Leonardo, which was carried to the ISS on space shuttle mission STS-102/ISS-5A.1. the ISS on space shuttle mission STS-102/ISS-5A.1. the ISS on space shuttle mission STS-102/ISS-5A.1.

Inside, there are racks of equipment and stowage items Inside, there are racks of equipment and stowage items Inside, there are racks of equipment and stowage items that the crew uses for daily living and specific experiments that the crew uses for daily living and specific experiments that the crew uses for daily living and specific experiments and procedures. When the materials have been used, and procedures. When the materials have been used, and procedures. When the materials have been used, the MPLM is then loaded with old equipment, racks, and the MPLM is then loaded with old equipment, racks, and the MPLM is then loaded with old equipment, racks, and other items no longer needed. The robotic arm returns other items no longer needed. The robotic arm returns other items no longer needed. The robotic arm returns the MPLM to the shuttle's cargo bay, and it makes the the MPLM to the shuttle's cargo bay, and it makes the the MPLM to the shuttle's cargo bay, and it makes the return trip home. return trip home. return trip home.

B-41 B-41 B-41 MPLM Raffaello is temporarily attached to Node 2 during MPLM Raffaello is temporarily attached to Node 2 during MPLM Raffaello is temporarily attached to Node 2 during its use on space shuttle mission STS-114/ISS-LF1. its use on space shuttle mission STS-114/ISS-LF1. its use on space shuttle mission STS-114/ISS-LF1.

The cylindrical modules can carry up to 15,000 lb of The cylindrical modules can carry up to 15,000 lb of The cylindrical modules can carry up to 15,000 lb of cargo, the equivalent of a semi-truck trailer, packed into 16 cargo, the equivalent of a semi-truck trailer, packed into 16 cargo, the equivalent of a semi-truck trailer, packed into 16 standard space station equipment racks. ISS racks aren't standard space station equipment racks. ISS racks aren't standard space station equipment racks. ISS racks aren't merely shelves, however. Racks on the ISS and space merely shelves, however. Racks on the ISS and space merely shelves, however. Racks on the ISS and space shuttle are self-contained cabinets that hold entire experi- shuttle are self-contained cabinets that hold entire experi- shuttle are self-contained cabinets that hold entire experi- ments or other projects. Each rack is a refrigerator-size ments or other projects. Each rack is a refrigerator-size ments or other projects. Each rack is a refrigerator-size carbon fiber box, and from there it can be customized to carbon fiber box, and from there it can be customized to carbon fiber box, and from there it can be customized to fit its need. Depending on the purpose of any given rack, fit its need. Depending on the purpose of any given rack, fit its need. Depending on the purpose of any given rack, the MPLM can be equipped with power, data, and fluid the MPLM can be equipped with power, data, and fluid the MPLM can be equipped with power, data, and fluid to support refrigerators or freezers, or it can be used to to support refrigerators or freezers, or it can be used to to support refrigerators or freezers, or it can be used to stow excess materials. In order to function as an attached stow excess materials. In order to function as an attached stow excess materials. In order to function as an attached ISS module as well as a cargo transport, the MPLM also ISS module as well as a cargo transport, the MPLM also ISS module as well as a cargo transport, the MPLM also includes components that provide some life support, fire includes components that provide some life support, fire includes components that provide some life support, fire detection and suppression, electrical distribution, and detection and suppression, electrical distribution, and detection and suppression, electrical distribution, and computer functions. computer functions. computer functions. Length: 21 ft (6.4 m) Length: 21 ft (6.4 m) Length: 21 ft (6.4 m) Width: 15 ft (4.6 m) Width: 15 ft (4.6 m) Width: 15 ft (4.6 m) Weight: 9,000 lb (4,082 kg) (empty) Weight: 9,000 lb (4,082 kg) (empty) Weight: 9,000 lb (4,082 kg) (empty) The Leonardo module was launched for the first time on The Leonardo module was launched for the first time on The Leonardo module was launched for the first time on space shuttle mission STS-102/ISS-5A.1. The Raffaello space shuttle mission STS-102/ISS-5A.1. The Raffaello space shuttle mission STS-102/ISS-5A.1. The Raffaello module was launched for the first time on space shuttle module was launched for the first time on space shuttle module was launched for the first time on space shuttle mission STS-100/ISS-6A. Donatello is not currently on mission STS-100/ISS-6A. Donatello is not currently on mission STS-100/ISS-6A. Donatello is not currently on the shuttle manifest to fly because of the cost associated the shuttle manifest to fly because of the cost associated the shuttle manifest to fly because of the cost associated with getting the module up to flight status code. There with getting the module up to flight status code. There with getting the module up to flight status code. There are only two MPLM flights scheduled before the station are only two MPLM flights scheduled before the station are only two MPLM flights scheduled before the station is complete. NASA is considering a European proposal is complete. NASA is considering a European proposal is complete. NASA is considering a European proposal to fit Donatello with enhanced micrometeroid protection to fit Donatello with enhanced micrometeroid protection to fit Donatello with enhanced micrometeroid protection and cooling systems and leaving it attached to the ISS and cooling systems and leaving it attached to the ISS and cooling systems and leaving it attached to the ISS after the space shuttle fleet is retired. after the space shuttle fleet is retired. after the space shuttle fleet is retired.

B-42 B-42 B-42 The Mobile Servicing System The Mobile Servicing System The Mobile Servicing System

Canada has contributed an element essential to the con- Canada has contributed an element essential to the con- Canada has contributed an element essential to the con- struction, operations, and maintenance of the ISS: the struction, operations, and maintenance of the ISS: the struction, operations, and maintenance of the ISS: the Mobile Servicing System (MSS). The MSS is composed of Mobile Servicing System (MSS). The MSS is composed of Mobile Servicing System (MSS). The MSS is composed of the Space Station Remote Manipulator System (SSRMS), the Space Station Remote Manipulator System (SSRMS), the Space Station Remote Manipulator System (SSRMS), the Mobile Base System (MBS), and the Special Purpose the Mobile Base System (MBS), and the Special Purpose the Mobile Base System (MBS), and the Special Purpose Dexterous Manipulator (SPDM). These three components Dexterous Manipulator (SPDM). These three components Dexterous Manipulator (SPDM). These three components have been designed to work together or independently. have been designed to work together or independently. have been designed to work together or independently.

The MSS, better known by its primary component Cana- The MSS, better known by its primary component Cana- The MSS, better known by its primary component Cana- darm2 (the SSRMS), is a robotic system that operates both darm2 (the SSRMS), is a robotic system that operates both darm2 (the SSRMS), is a robotic system that operates both autonomously or under astronaut control. It plays a key role autonomously or under astronaut control. It plays a key role autonomously or under astronaut control. It plays a key role in station assembly and maintenance: moving equipment in station assembly and maintenance: moving equipment in station assembly and maintenance: moving equipment and supplies around the station, supporting astronauts and supplies around the station, supporting astronauts and supplies around the station, supporting astronauts working in space, and servicing instruments and other working in space, and servicing instruments and other working in space, and servicing instruments and other payloads attached to the space station. payloads attached to the space station. payloads attached to the space station.

Launched on STS-100, the next-generation Canadarm2 Launched on STS-100, the next-generation Canadarm2 Launched on STS-100, the next-generation Canadarm2 is a bigger, more versatile version of the space shuttle's is a bigger, more versatile version of the space shuttle's is a bigger, more versatile version of the space shuttle's robotic arm. Canadarm2 is capable of handling large robotic arm. Canadarm2 is capable of handling large robotic arm. Canadarm2 is capable of handling large payloads of up to 256,000 lb (116,000 kg). payloads of up to 256,000 lb (116,000 kg). payloads of up to 256,000 lb (116,000 kg). Length: 57.7 ft (17.6 m) Length: 57.7 ft (17.6 m) Length: 57.7 ft (17.6 m) Width: 13.8 in. (35 cm) Width: 13.8 in. (35 cm) Width: 13.8 in. (35 cm) Weight: 3,618 lb (1,800 kg) Weight: 3,618 lb (1,800 kg) Weight: 3,618 lb (1,800 kg) It has seven motorized joints and can move end-over-end It has seven motorized joints and can move end-over-end It has seven motorized joints and can move end-over-end in an inchworm-like movement to reach many parts of the in an inchworm-like movement to reach many parts of the in an inchworm-like movement to reach many parts of the space station, locking its free end on one of many special space station, locking its free end on one of many special space station, locking its free end on one of many special fixtures called Power and Data Grapple Fixtures (PDGFs) fixtures called Power and Data Grapple Fixtures (PDGFs) fixtures called Power and Data Grapple Fixtures (PDGFs) and then detaching its other end and pivoting it forward. In and then detaching its other end and pivoting it forward. In and then detaching its other end and pivoting it forward. In this movement, it is limited only by the number of PDGFs this movement, it is limited only by the number of PDGFs this movement, it is limited only by the number of PDGFs on the station. PDGFs placed strategically around the sta- on the station. PDGFs placed strategically around the sta- on the station. PDGFs placed strategically around the sta- tion provide power, data, and video to the arm through its tion provide power, data, and video to the arm through its tion provide power, data, and video to the arm through its latching end effectors (LEEs). Its speed when unloaded latching end effectors (LEEs). Its speed when unloaded latching end effectors (LEEs). Its speed when unloaded is 1.21 ft/sec (37 cm/sec) and when loaded (for station is 1.21 ft/sec (37 cm/sec) and when loaded (for station is 1.21 ft/sec (37 cm/sec) and when loaded (for station assembly) is 0.79 in./sec (2 cm/sec). assembly) is 0.79 in./sec (2 cm/sec). assembly) is 0.79 in./sec (2 cm/sec).

B-43 B-43 B-43 STS-114/ISS-LF1 mission specialist Stephen K. Robinson, STS-114/ISS-LF1 mission specialist Stephen K. Robinson, STS-114/ISS-LF1 mission specialist Stephen K. Robinson, anchored to a foot restraint on Canadarm2, participates in anchored to a foot restraint on Canadarm2, participates in anchored to a foot restraint on Canadarm2, participates in an EVA. an EVA. an EVA.

The Mobile Base System (MBS), a moveable work platform The Mobile Base System (MBS), a moveable work platform The Mobile Base System (MBS), a moveable work platform added to the station during STS-111, and the U.S.-provided added to the station during STS-111, and the U.S.-provided added to the station during STS-111, and the U.S.-provided Mobile Transporter (MT), installed during STS-110, glide Mobile Transporter (MT), installed during STS-110, glide Mobile Transporter (MT), installed during STS-110, glide down rails on the station's trusses, putting much of the down rails on the station's trusses, putting much of the down rails on the station's trusses, putting much of the station within grasp of the arm. When Canadarm2 is at- station within grasp of the arm. When Canadarm2 is at- station within grasp of the arm. When Canadarm2 is at- tached to the MBS, it has the ability to travel to work sites tached to the MBS, it has the ability to travel to work sites tached to the MBS, it has the ability to travel to work sites all along the truss structure. Astronauts also use the MBS all along the truss structure. Astronauts also use the MBS all along the truss structure. Astronauts also use the MBS as a platform from which to perform spacewalks as well as as a platform from which to perform spacewalks as well as as a platform from which to perform spacewalks as well as a storage facility where they can keep various tools. a storage facility where they can keep various tools. a storage facility where they can keep various tools.

B-44 B-44 B-44 The MBS is moved by Canadarm2 for installation on the The MBS is moved by Canadarm2 for installation on the The MBS is moved by Canadarm2 for installation on the ISS during space shuttle mission STS-111/ISS-UF2. ISS during space shuttle mission STS-111/ISS-UF2. ISS during space shuttle mission STS-111/ISS-UF2.

Since the MBS has four PDGFs, it can serve as a base for Since the MBS has four PDGFs, it can serve as a base for Since the MBS has four PDGFs, it can serve as a base for both Canadarm2 and the SPDM simultaneously. Through both Canadarm2 and the SPDM simultaneously. Through both Canadarm2 and the SPDM simultaneously. Through these anchor points, the MBS provides power and data these anchor points, the MBS provides power and data these anchor points, the MBS provides power and data to the robotics as well as to the payloads that they may to the robotics as well as to the payloads that they may to the robotics as well as to the payloads that they may be supporting. be supporting. be supporting. Length: 18.7 ft (5.7 m) Length: 18.7 ft (5.7 m) Length: 18.7 ft (5.7 m) Width: 14.8 ft (4.5 m) Width: 14.8 ft (4.5 m) Width: 14.8 ft (4.5 m) Weight: 3,197 lb (1,450 kg) Weight: 3,197 lb (1,450 kg) Weight: 3,197 lb (1,450 kg) The high-strength aluminum and titanium MT—the first The high-strength aluminum and titanium MT—the first The high-strength aluminum and titanium MT—the first railroad in space—has a payload capacity of 46,100 lb railroad in space—has a payload capacity of 46,100 lb railroad in space—has a payload capacity of 46,100 lb (20,911 kg). Its top speed is about 1 in./sec. The MT is (20,911 kg). Its top speed is about 1 in./sec. The MT is (20,911 kg). Its top speed is about 1 in./sec. The MT is prevented from separating from the ISS In the microgravity prevented from separating from the ISS In the microgravity prevented from separating from the ISS In the microgravity environment of space by using wheels that are both under environment of space by using wheels that are both under environment of space by using wheels that are both under and above the tracks, similar to a suspension roller coaster and above the tracks, similar to a suspension roller coaster and above the tracks, similar to a suspension roller coaster at an amusement park. The MT is controlled by complex at an amusement park. The MT is controlled by complex at an amusement park. The MT is controlled by complex software that dictates its movements. When the MT stops software that dictates its movements. When the MT stops software that dictates its movements. When the MT stops at work sites along the line, it can be locked down with a at work sites along the line, it can be locked down with a at work sites along the line, it can be locked down with a 7,000-lb grip to hold it in place so Canadarm2 can safely 7,000-lb grip to hold it in place so Canadarm2 can safely 7,000-lb grip to hold it in place so Canadarm2 can safely maneuver cargo. Although it can be driven from on board maneuver cargo. Although it can be driven from on board maneuver cargo. Although it can be driven from on board the station, the flight controllers in the Mission Control the station, the flight controllers in the Mission Control the station, the flight controllers in the Mission Control Center in Houston often drive the train from thousands of Center in Houston often drive the train from thousands of Center in Houston often drive the train from thousands of miles away and hundreds of miles below. miles away and hundreds of miles below. miles away and hundreds of miles below. Length: 9 ft (2.7 m) Length: 9 ft (2.7 m) Length: 9 ft (2.7 m) Width: 8.6 ft (2.6 m) Width: 8.6 ft (2.6 m) Width: 8.6 ft (2.6 m) Weight: 1,950 lb (885 kg) Weight: 1,950 lb (885 kg) Weight: 1,950 lb (885 kg) The Special Purpose Dexterous Manipulator, also known The Special Purpose Dexterous Manipulator, also known The Special Purpose Dexterous Manipulator, also known as Dextre or the Canada hand, is a highly advanced two- as Dextre or the Canada hand, is a highly advanced two- as Dextre or the Canada hand, is a highly advanced two- armed robot. It can work solo, fixed to one of the PDGFs armed robot. It can work solo, fixed to one of the PDGFs armed robot. It can work solo, fixed to one of the PDGFs on the station, or on the MBS. Most of the time, Dextre will on the station, or on the MBS. Most of the time, Dextre will on the station, or on the MBS. Most of the time, Dextre will do its work while attached to the free end of Canadarm2, do its work while attached to the free end of Canadarm2, do its work while attached to the free end of Canadarm2, which will maneuver Dextre into position next to the pay- which will maneuver Dextre into position next to the pay- which will maneuver Dextre into position next to the pay- load that requires maintenance. Dextre can be operated load that requires maintenance. Dextre can be operated load that requires maintenance. Dextre can be operated by crew members inside the ISS or by flight controllers by crew members inside the ISS or by flight controllers by crew members inside the ISS or by flight controllers on the ground. on the ground. on the ground.

B-45 B-45 B-45 Dextre in the grasp of Canadarm2 Dextre in the grasp of Canadarm2 Dextre in the grasp of Canadarm2

Dextre resembles a headless torso fitted with two ex- Dextre resembles a headless torso fitted with two ex- Dextre resembles a headless torso fitted with two ex- tremely agile arms and several smaller appendages. tremely agile arms and several smaller appendages. tremely agile arms and several smaller appendages. The two arms each have seven specially offset joints The two arms each have seven specially offset joints The two arms each have seven specially offset joints that give tremendous freedom of movement. At the end that give tremendous freedom of movement. At the end that give tremendous freedom of movement. At the end of each of the arms is the Orbital Replacement Unit/Tool of each of the arms is the Orbital Replacement Unit/Tool of each of the arms is the Orbital Replacement Unit/Tool Changeout Mechanism (OTCM), which provides built-in Changeout Mechanism (OTCM), which provides built-in Changeout Mechanism (OTCM), which provides built-in grasping jaws, a retractable socket drive, a monochrome grasping jaws, a retractable socket drive, a monochrome grasping jaws, a retractable socket drive, a monochrome TV camera, lights, and umbilical connectors. The lower TV camera, lights, and umbilical connectors. The lower TV camera, lights, and umbilical connectors. The lower torso has a pair of color TV cameras, an ORU platform, torso has a pair of color TV cameras, an ORU platform, torso has a pair of color TV cameras, an ORU platform, and tool holders. The torso pivots at the waist to perform and tool holders. The torso pivots at the waist to perform and tool holders. The torso pivots at the waist to perform sophisticated operations, including installing and remov- sophisticated operations, including installing and remov- sophisticated operations, including installing and remov- ing small payloads such as batteries, supplies, and ing small payloads such as batteries, supplies, and ing small payloads such as batteries, supplies, and computers. It can also handle tools such as specialized computers. It can also handle tools such as specialized computers. It can also handle tools such as specialized wrenches and socket extensions for delicate maintenance wrenches and socket extensions for delicate maintenance wrenches and socket extensions for delicate maintenance and servicing tasks. and servicing tasks. and servicing tasks. Length: 11.5 ft (3.5 m) Length: 11.5 ft (3.5 m) Length: 11.5 ft (3.5 m) Width: 7.7 ft (2.3 m) Width: 7.7 ft (2.3 m) Width: 7.7 ft (2.3 m) Weight: 3,664 lb (1,662 kg) Weight: 3,664 lb (1,662 kg) Weight: 3,664 lb (1,662 kg)

Crew and Equipment Translation Aid Crew and Equipment Translation Aid Crew and Equipment Translation Aid

Spacewalking crew members needed a work platform that Spacewalking crew members needed a work platform that Spacewalking crew members needed a work platform that could provide them with a means of transporting them- could provide them with a means of transporting them- could provide them with a means of transporting them- selves, tools, and orbital replacement units (ORUs) safely selves, tools, and orbital replacement units (ORUs) safely selves, tools, and orbital replacement units (ORUs) safely and easily along the ISS truss structure. The Lockheed and easily along the ISS truss structure. The Lockheed and easily along the ISS truss structure. The Lockheed Martin-built Crew and Equipment Translation Aid (CETA)— Martin-built Crew and Equipment Translation Aid (CETA)— Martin-built Crew and Equipment Translation Aid (CETA)— one of the largest pieces of EVA equipment built for the one of the largest pieces of EVA equipment built for the one of the largest pieces of EVA equipment built for the ISS—is NASA’s equivalent of a flatbed truck. ISS—is NASA’s equivalent of a flatbed truck. ISS—is NASA’s equivalent of a flatbed truck. Length: 8.25 ft (2.5 m) Length: 8.25 ft (2.5 m) Length: 8.25 ft (2.5 m) Width: 7.75 ft (2.4 m) Width: 7.75 ft (2.4 m) Width: 7.75 ft (2.4 m) Weight: 623 lb (283 kg) Weight: 623 lb (283 kg) Weight: 623 lb (283 kg) Two CETAs were launched in 2002 as integrated parts Two CETAs were launched in 2002 as integrated parts Two CETAs were launched in 2002 as integrated parts of the S1 and P1 truss segments. The first CETA was of the S1 and P1 truss segments. The first CETA was of the S1 and P1 truss segments. The first CETA was launched on STS-112, station assembly flight 9A. The launched on STS-112, station assembly flight 9A. The launched on STS-112, station assembly flight 9A. The second CETA was launched on STS-113, station assembly second CETA was launched on STS-113, station assembly second CETA was launched on STS-113, station assembly flight 11A. flight 11A. flight 11A.

B-46 B-46 B-46 Crew members can propel themselves and accompanying Crew members can propel themselves and accompanying Crew members can propel themselves and accompanying hardware manually along the Mobile Transporter (MT) rails, hardware manually along the Mobile Transporter (MT) rails, hardware manually along the Mobile Transporter (MT) rails, which run the length of the truss structure. The two CETA which run the length of the truss structure. The two CETA which run the length of the truss structure. The two CETA carts are located one on each side of the MT for usage carts are located one on each side of the MT for usage carts are located one on each side of the MT for usage flexibility. If required, a cart may be moved to the other side flexibility. If required, a cart may be moved to the other side flexibility. If required, a cart may be moved to the other side of the MT to complement the other cart. A CETA cart can of the MT to complement the other cart. A CETA cart can of the MT to complement the other cart. A CETA cart can be used alone or coupled to the MT. When not in use, the be used alone or coupled to the MT. When not in use, the be used alone or coupled to the MT. When not in use, the CETAs attach to the MT for stowage. CETAs attach to the MT for stowage. CETAs attach to the MT for stowage.

Mission specialist John Herrington, anchored on Mission specialist John Herrington, anchored on Mission specialist John Herrington, anchored on Canadarm2, moves the CETA during an STS-113/ISS-11A Canadarm2, moves the CETA during an STS-113/ISS-11A Canadarm2, moves the CETA during an STS-113/ISS-11A EVA. EVA. EVA.

The CETAs have attachment points for other EVA hardware The CETAs have attachment points for other EVA hardware The CETAs have attachment points for other EVA hardware such as the ORU Transfer Device (OTD), also known as the such as the ORU Transfer Device (OTD), also known as the such as the ORU Transfer Device (OTD), also known as the Space Crane; Articulating Portable Foot Restraint (APFR); Space Crane; Articulating Portable Foot Restraint (APFR); Space Crane; Articulating Portable Foot Restraint (APFR); EVA Tool Stowage Device (ETSD); and a host of other small EVA Tool Stowage Device (ETSD); and a host of other small EVA Tool Stowage Device (ETSD); and a host of other small crew and equipment restraining tools. During ISS assem- crew and equipment restraining tools. During ISS assem- crew and equipment restraining tools. During ISS assem- bly operations, crew members also use CETA as a work bly operations, crew members also use CETA as a work bly operations, crew members also use CETA as a work platform to reach 90 percent of the work sites safely. platform to reach 90 percent of the work sites safely. platform to reach 90 percent of the work sites safely.

CETA is made of many components, including the follow- CETA is made of many components, including the follow- CETA is made of many components, including the follow- ing major subassemblies: ing major subassemblies: ing major subassemblies: • A 142-lb (64 kg) main frame • A 142-lb (64 kg) main frame • A 142-lb (64 kg) main frame • A 126-lb (57 kg) toolbox to stow EVA tools • A 126-lb (57 kg) toolbox to stow EVA tools • A 126-lb (57 kg) toolbox to stow EVA tools • Launch restraints to ensure CETA is secured to the • Launch restraints to ensure CETA is secured to the • Launch restraints to ensure CETA is secured to the truss segment truss segment truss segment • A wheel/brake subsystem to move along the truss • A wheel/brake subsystem to move along the truss • A wheel/brake subsystem to move along the truss • A dynamic brake for speed control and a parking brake • A dynamic brake for speed control and a parking brake • A dynamic brake for speed control and a parking brake for use at work sites for use at work sites for use at work sites • Energy absorbers to reduce the impact of a hard • Energy absorbers to reduce the impact of a hard • Energy absorbers to reduce the impact of a hard stop stop stop • Three swing arms to provide access to structures • Three swing arms to provide access to structures • Three swing arms to provide access to structures alongside the truss alongside the truss alongside the truss • An ORU transfer flat bed for attaching ORUs • An ORU transfer flat bed for attaching ORUs • An ORU transfer flat bed for attaching ORUs

B-47 B-47 B-47 ISS Electrical Power System ISS Electrical Power System ISS Electrical Power System During STS-116, spacewalking astronauts performed the During STS-116, spacewalking astronauts performed the During STS-116, spacewalking astronauts performed the equivalent of rewiring the station’s Electrical Power System equivalent of rewiring the station’s Electrical Power System equivalent of rewiring the station’s Electrical Power System (EPS). The astronauts, along with Boeing engineers and (EPS). The astronauts, along with Boeing engineers and (EPS). The astronauts, along with Boeing engineers and NASA mission controllers, orchestrated a precise ballet NASA mission controllers, orchestrated a precise ballet NASA mission controllers, orchestrated a precise ballet of powering down equipment, transferring it over to other of powering down equipment, transferring it over to other of powering down equipment, transferring it over to other redundant power channels, and then unplugging and redundant power channels, and then unplugging and redundant power channels, and then unplugging and plugging in electrical connectors. plugging in electrical connectors. plugging in electrical connectors. The ISS power system was transitioned from its temporary The ISS power system was transitioned from its temporary The ISS power system was transitioned from its temporary system to its permanent configuration by rerouting power system to its permanent configuration by rerouting power system to its permanent configuration by rerouting power through electrical components on its port 1, starboard through electrical components on its port 1, starboard through electrical components on its port 1, starboard 0, and starboard 1 trusses for the first time. Like a city’s 0, and starboard 1 trusses for the first time. Like a city’s 0, and starboard 1 trusses for the first time. Like a city’s central power plant, the station’s giant solar arrays gen- central power plant, the station’s giant solar arrays gen- central power plant, the station’s giant solar arrays gen- erate primary ISS power at levels too high for consumer erate primary ISS power at levels too high for consumer erate primary ISS power at levels too high for consumer use, ranging from 137 to 173 Vdc. The power is regulated use, ranging from 137 to 173 Vdc. The power is regulated use, ranging from 137 to 173 Vdc. The power is regulated between 150 to 160 volts, then routed to batteries for between 150 to 160 volts, then routed to batteries for between 150 to 160 volts, then routed to batteries for storage and to switching units that route it to distribution storage and to switching units that route it to distribution storage and to switching units that route it to distribution networks. The power coming from the solar arrays and networks. The power coming from the solar arrays and networks. The power coming from the solar arrays and batteries is called primary power. batteries is called primary power. batteries is called primary power. The primary power is routed to the four main bus switching The primary power is routed to the four main bus switching The primary power is routed to the four main bus switching units located on the S0 truss. The MBSUs are fed by eight units located on the S0 truss. The MBSUs are fed by eight units located on the S0 truss. The MBSUs are fed by eight independent power channels (corresponding to each of independent power channels (corresponding to each of independent power channels (corresponding to each of the eight solar array wings), and the MBSUs output all the eight solar array wings), and the MBSUs output all the eight solar array wings), and the MBSUs output all ISS loads. Under normal operations, each power channel ISS loads. Under normal operations, each power channel ISS loads. Under normal operations, each power channel supplies power to a specific set of loads. However, if that supplies power to a specific set of loads. However, if that supplies power to a specific set of loads. However, if that channel fails, the MBSUs enable feeding power to those channel fails, the MBSUs enable feeding power to those channel fails, the MBSUs enable feeding power to those loads from another channel, which greatly enhances the loads from another channel, which greatly enhances the loads from another channel, which greatly enhances the fault tolerance of the EPS. fault tolerance of the EPS. fault tolerance of the EPS. DC-to-DC converters “step-down” the primary 160-Vdc DC-to-DC converters “step-down” the primary 160-Vdc DC-to-DC converters “step-down” the primary 160-Vdc electricity to a more tightly regulated secondary power electricity to a more tightly regulated secondary power electricity to a more tightly regulated secondary power of 124.5 Vdc and distribute it to individual users. On Main of 124.5 Vdc and distribute it to individual users. On Main of 124.5 Vdc and distribute it to individual users. On Main Street USA, the users would be shops and homes. On Street USA, the users would be shops and homes. On Street USA, the users would be shops and homes. On the ISS, they are laboratories, living quarters, and the like. the ISS, they are laboratories, living quarters, and the like. the ISS, they are laboratories, living quarters, and the like. This secondary power feeds all the loads on the station. This secondary power feeds all the loads on the station. This secondary power feeds all the loads on the station. Most “electronics” such as laptops within the labs, nodes, Most “electronics” such as laptops within the labs, nodes, Most “electronics” such as laptops within the labs, nodes, airlocks, and living areas use even lower voltage stepped airlocks, and living areas use even lower voltage stepped airlocks, and living areas use even lower voltage stepped down via power supplies. down via power supplies. down via power supplies. The space shuttle and most other spacecraft operate at The space shuttle and most other spacecraft operate at The space shuttle and most other spacecraft operate at 28 Vdc, as does the Russian ISS segment, which has its 28 Vdc, as does the Russian ISS segment, which has its 28 Vdc, as does the Russian ISS segment, which has its own two sets of solar arrays but can use and share U.S. own two sets of solar arrays but can use and share U.S. own two sets of solar arrays but can use and share U.S. power by using converters. The higher voltage of the U.S. power by using converters. The higher voltage of the U.S. power by using converters. The higher voltage of the U.S. power system will meet the higher overall ISS requirements power system will meet the higher overall ISS requirements power system will meet the higher overall ISS requirements for research as a test power bed for exploration while for research as a test power bed for exploration while for research as a test power bed for exploration while permitting use of smaller, lighter weight power lines. The permitting use of smaller, lighter weight power lines. The permitting use of smaller, lighter weight power lines. The higher voltage also reduces ohmic power losses through higher voltage also reduces ohmic power losses through higher voltage also reduces ohmic power losses through the wires. the wires. the wires. Even though the station will spend about one-third of every Even though the station will spend about one-third of every Even though the station will spend about one-third of every orbit in the Earth’s shadow, the electrical power system orbit in the Earth’s shadow, the electrical power system orbit in the Earth’s shadow, the electrical power system can continuously provide 84-120 kW of usable power to can continuously provide 84-120 kW of usable power to can continuously provide 84-120 kW of usable power to ISS systems using all eight solar array wings. Boeing’s ISS systems using all eight solar array wings. Boeing’s ISS systems using all eight solar array wings. Boeing’s Rocketdyne Propulsion and Power division (now Hamilton Rocketdyne Propulsion and Power division (now Hamilton Rocketdyne Propulsion and Power division (now Hamilton Sundstrand) built most of the EPS hardware. Boeing, along Sundstrand) built most of the EPS hardware. Boeing, along Sundstrand) built most of the EPS hardware. Boeing, along with Hamilton Sundstrand as a subcontractor, provides with Hamilton Sundstrand as a subcontractor, provides with Hamilton Sundstrand as a subcontractor, provides EPS sustaining engineering support to NASA. EPS sustaining engineering support to NASA. EPS sustaining engineering support to NASA.

B-48 B-48 B-48 Active Thermal Control System Overview Active Thermal Control System Overview Active Thermal Control System Overview

Most of the station’s many systems produce waste heat, Most of the station’s many systems produce waste heat, Most of the station’s many systems produce waste heat, which needs to be transferred from the ISS to space to which needs to be transferred from the ISS to space to which needs to be transferred from the ISS to space to achieve thermal control and maintain electrical compo- achieve thermal control and maintain electrical compo- achieve thermal control and maintain electrical compo- nents at acceptable temperatures. An Active Thermal nents at acceptable temperatures. An Active Thermal nents at acceptable temperatures. An Active Thermal Control System (ATCS) is required to achieve this heat Control System (ATCS) is required to achieve this heat Control System (ATCS) is required to achieve this heat rejection function when the combination of the ISS exter- rejection function when the combination of the ISS exter- rejection function when the combination of the ISS exter- nal environment and the generated heat loads exceeds nal environment and the generated heat loads exceeds nal environment and the generated heat loads exceeds the capabilities of the Passive Thermal Control System the capabilities of the Passive Thermal Control System the capabilities of the Passive Thermal Control System to maintain temperatures. An ATCS uses a mechanically to maintain temperatures. An ATCS uses a mechanically to maintain temperatures. An ATCS uses a mechanically pumped fluid in closed-loop circuits to perform three pumped fluid in closed-loop circuits to perform three pumped fluid in closed-loop circuits to perform three functions: heat collection, heat transportation, and heat functions: heat collection, heat transportation, and heat functions: heat collection, heat transportation, and heat rejection. Waste heat is removed in two ways: through rejection. Waste heat is removed in two ways: through rejection. Waste heat is removed in two ways: through coldplates and heat exchangers, both of which are cooled coldplates and heat exchangers, both of which are cooled coldplates and heat exchangers, both of which are cooled by circulating ammonia loops on the outside of the sta- by circulating ammonia loops on the outside of the sta- by circulating ammonia loops on the outside of the sta- tion. Ammonia is used because of its low freezing point. tion. Ammonia is used because of its low freezing point. tion. Ammonia is used because of its low freezing point. The heated ammonia circulates through large radiators The heated ammonia circulates through large radiators The heated ammonia circulates through large radiators located on the exterior of the ISS, releasing the heat by located on the exterior of the ISS, releasing the heat by located on the exterior of the ISS, releasing the heat by radiation to space that cools the ammonia as it flows radiation to space that cools the ammonia as it flows radiation to space that cools the ammonia as it flows through the radiators. through the radiators. through the radiators.

The ATCS consists of the Internal Active Thermal Control The ATCS consists of the Internal Active Thermal Control The ATCS consists of the Internal Active Thermal Control System (IATCS), External Active Thermal Control System System (IATCS), External Active Thermal Control System System (IATCS), External Active Thermal Control System (EATCS), Photovoltaic Thermal Control System (PVTCS), (EATCS), Photovoltaic Thermal Control System (PVTCS), (EATCS), Photovoltaic Thermal Control System (PVTCS), and Early External Active Thermal Control System (EE- and Early External Active Thermal Control System (EE- and Early External Active Thermal Control System (EE- ATCS). The IATCS consists of loops that circulate water ATCS). The IATCS consists of loops that circulate water ATCS). The IATCS consists of loops that circulate water through the interior of the U.S. Laboratory module to collect through the interior of the U.S. Laboratory module to collect through the interior of the U.S. Laboratory module to collect the excess heat from electronic and experiment equipment the excess heat from electronic and experiment equipment the excess heat from electronic and experiment equipment and distributes this heat to the interface heat exchangers and distributes this heat to the interface heat exchangers and distributes this heat to the interface heat exchangers for transfer to the EATCS. At assembly complete, there for transfer to the EATCS. At assembly complete, there for transfer to the EATCS. At assembly complete, there will be nine separate IATCS water loops in the U.S. and will be nine separate IATCS water loops in the U.S. and will be nine separate IATCS water loops in the U.S. and international partner pressurized modules. international partner pressurized modules. international partner pressurized modules.

The Photovoltaic Thermal Control System (PVTCS) con- The Photovoltaic Thermal Control System (PVTCS) con- The Photovoltaic Thermal Control System (PVTCS) con- sists of ammonia loops that collect excess heat from sists of ammonia loops that collect excess heat from sists of ammonia loops that collect excess heat from the Electrical Power System (EPS) components in the the Electrical Power System (EPS) components in the the Electrical Power System (EPS) components in the Integrated Equipment Assembly (IEA) on P4 and S4 and Integrated Equipment Assembly (IEA) on P4 and S4 and Integrated Equipment Assembly (IEA) on P4 and S4 and transport this heat to the PV radiators (located on P4, P6, transport this heat to the PV radiators (located on P4, P6, transport this heat to the PV radiators (located on P4, P6, S4, and S6) where it is rejected to space. The PVTCS S4, and S6) where it is rejected to space. The PVTCS S4, and S6) where it is rejected to space. The PVTCS consists of ammonia coolant, 11 coldplates, two pump consists of ammonia coolant, 11 coldplates, two pump consists of ammonia coolant, 11 coldplates, two pump flow control subassemblies (PFCS), and one photovoltaic flow control subassemblies (PFCS), and one photovoltaic flow control subassemblies (PFCS), and one photovoltaic radiator (PVR). radiator (PVR). radiator (PVR).

The External Active Thermal Control System (EATCS), The External Active Thermal Control System (EATCS), The External Active Thermal Control System (EATCS), activated for the first time on STS-116, consists of ammonia activated for the first time on STS-116, consists of ammonia activated for the first time on STS-116, consists of ammonia loops to collect heat from the interface heat exchangers loops to collect heat from the interface heat exchangers loops to collect heat from the interface heat exchangers and external electronic equipment mounted on coldplates and external electronic equipment mounted on coldplates and external electronic equipment mounted on coldplates and transports it to the S1 and P1 radiators where it is and transports it to the S1 and P1 radiators where it is and transports it to the S1 and P1 radiators where it is rejected to space. In lieu of using the EATCS initially, the rejected to space. In lieu of using the EATCS initially, the rejected to space. In lieu of using the EATCS initially, the station hardware has been cooled by the Early External station hardware has been cooled by the Early External station hardware has been cooled by the Early External Active Thermal Control System (EEATCS). The EEATCS Active Thermal Control System (EEATCS). The EEATCS Active Thermal Control System (EEATCS). The EEATCS provided heat rejection capability for the U.S. Laboratory provided heat rejection capability for the U.S. Laboratory provided heat rejection capability for the U.S. Laboratory interface heat exchangers (IFHX) from assembly flight 5A interface heat exchangers (IFHX) from assembly flight 5A interface heat exchangers (IFHX) from assembly flight 5A through 12A.1. through 12A.1. through 12A.1.

B-49 B-49 B-49 The EEATCS is the temporary system used to collect, The EEATCS is the temporary system used to collect, The EEATCS is the temporary system used to collect, transport, and reject waste heat from habitable volumes transport, and reject waste heat from habitable volumes transport, and reject waste heat from habitable volumes on the station. The EEATCS collects heat from the IFHX on the station. The EEATCS collects heat from the IFHX on the station. The EEATCS collects heat from the IFHX located on the U.S. Laboratory module, circulates the located on the U.S. Laboratory module, circulates the located on the U.S. Laboratory module, circulates the working fluid, anhydrous ammonia, via the pump and flow working fluid, anhydrous ammonia, via the pump and flow working fluid, anhydrous ammonia, via the pump and flow control subassembly (PFCS), and rejects heat to space via control subassembly (PFCS), and rejects heat to space via control subassembly (PFCS), and rejects heat to space via two orthogonally oriented stationary radiators. two orthogonally oriented stationary radiators. two orthogonally oriented stationary radiators.

Radiator ORU (8 panels) Radiator ORU (8 panels) Radiator ORU (8 panels)

Radiator beam Radiator beam Radiator beam

Note: All three radiators shown deployed. Note: All three radiators shown deployed. Note: All three radiators shown deployed.

ISS Flight Software ISS Flight Software ISS Flight Software

Flight software on board the ISS runs autonomously for Flight software on board the ISS runs autonomously for Flight software on board the ISS runs autonomously for the most part and provides critical functionality to maintain the most part and provides critical functionality to maintain the most part and provides critical functionality to maintain station life support systems, navigation and control, and station life support systems, navigation and control, and station life support systems, navigation and control, and communications with both the ground and the onboard communications with both the ground and the onboard communications with both the ground and the onboard crew. crew. crew.

Nothing on the station moves unless it is told by the soft- Nothing on the station moves unless it is told by the soft- Nothing on the station moves unless it is told by the soft- ware to do so. For the ISS to maintain orbital altitude, com- ware to do so. For the ISS to maintain orbital altitude, com- ware to do so. For the ISS to maintain orbital altitude, com- mands from the Russian segment computer tell thrusters mands from the Russian segment computer tell thrusters mands from the Russian segment computer tell thrusters on the Service Module or attached Progress supply ship on the Service Module or attached Progress supply ship on the Service Module or attached Progress supply ship to fire. For the giant solar arrays to track the sun, com- to fire. For the giant solar arrays to track the sun, com- to fire. For the giant solar arrays to track the sun, com- mands are sent from the U.S. computers responsible for mands are sent from the U.S. computers responsible for mands are sent from the U.S. computers responsible for the power generation function. For the station robotic arm the power generation function. For the station robotic arm the power generation function. For the station robotic arm to reach out and grapple a nearby element alongside the to reach out and grapple a nearby element alongside the to reach out and grapple a nearby element alongside the station, commands are sent from the Canadian robotics station, commands are sent from the Canadian robotics station, commands are sent from the Canadian robotics computers. computers. computers.

Not only the big moving parts but also the unseen equip- Not only the big moving parts but also the unseen equip- Not only the big moving parts but also the unseen equip- ment responsible for life support—oxygen generation ment responsible for life support—oxygen generation ment responsible for life support—oxygen generation equipment, water processors, carbon dioxide removal equipment, water processors, carbon dioxide removal equipment, water processors, carbon dioxide removal equipment, and scores of other devices—are monitored equipment, and scores of other devices—are monitored equipment, and scores of other devices—are monitored and commanded by the multitude of onboard computers. and commanded by the multitude of onboard computers. and commanded by the multitude of onboard computers.

This software has been built in countries around the This software has been built in countries around the This software has been built in countries around the globe—Russia, Germany, France, Canada, Italy, Japan, globe—Russia, Germany, France, Canada, Italy, Japan, globe—Russia, Germany, France, Canada, Italy, Japan, and the United States—by the various partner space and the United States—by the various partner space and the United States—by the various partner space agencies and their contractors. Currently, more than 50 agencies and their contractors. Currently, more than 50 agencies and their contractors. Currently, more than 50 dedicated computers, plus a score of crew member laptop dedicated computers, plus a score of crew member laptop dedicated computers, plus a score of crew member laptop

B-50 B-50 B-50 computers, are interconnected across a very large network computers, are interconnected across a very large network computers, are interconnected across a very large network to provide critical command and control functions. In all, to provide critical command and control functions. In all, to provide critical command and control functions. In all, there are about 7.5 million source lines of software code there are about 7.5 million source lines of software code there are about 7.5 million source lines of software code resident on these computers, even if one does not count resident on these computers, even if one does not count resident on these computers, even if one does not count the more common Microsoft operating systems and ap- the more common Microsoft operating systems and ap- the more common Microsoft operating systems and ap- plications running on the crew laptops. plications running on the crew laptops. plications running on the crew laptops.

Software development for the ISS is a unique challenge Software development for the ISS is a unique challenge Software development for the ISS is a unique challenge because it is an international effort, brought together on because it is an international effort, brought together on because it is an international effort, brought together on orbit in a phased manner and built to the most exacting orbit in a phased manner and built to the most exacting orbit in a phased manner and built to the most exacting standards to ensure crew safety. Software within each standards to ensure crew safety. Software within each standards to ensure crew safety. Software within each computer is qualified at the site where developed, and computer is qualified at the site where developed, and computer is qualified at the site where developed, and then further integrated testing is performed in Houston then further integrated testing is performed in Houston then further integrated testing is performed in Houston with all associated partner software. This NASA facility, with all associated partner software. This NASA facility, with all associated partner software. This NASA facility, the International Space Station Software Development the International Space Station Software Development the International Space Station Software Development and Integration Laboratory, sits alongside the large Neutral and Integration Laboratory, sits alongside the large Neutral and Integration Laboratory, sits alongside the large Neutral Buoyancy Pool where astronauts train for their missions. Buoyancy Pool where astronauts train for their missions. Buoyancy Pool where astronauts train for their missions. The laboratory provides the ability to test the integrated The laboratory provides the ability to test the integrated The laboratory provides the ability to test the integrated station software in an environment as close as possible station software in an environment as close as possible station software in an environment as close as possible to the real one on orbit. To the maximum extent possible, to the real one on orbit. To the maximum extent possible, to the real one on orbit. To the maximum extent possible, the laboratory uses flight-equivalent computers, power, the laboratory uses flight-equivalent computers, power, the laboratory uses flight-equivalent computers, power, and wiring connections to ensure that the system timing and wiring connections to ensure that the system timing and wiring connections to ensure that the system timing and interface conditions will be realistic. This exactness is and interface conditions will be realistic. This exactness is and interface conditions will be realistic. This exactness is a necessity, as the software must work correctly from the a necessity, as the software must work correctly from the a necessity, as the software must work correctly from the first moment it becomes operational on orbit. Failure of the first moment it becomes operational on orbit. Failure of the first moment it becomes operational on orbit. Failure of the software could pose a risk to crew safety and continued software could pose a risk to crew safety and continued software could pose a risk to crew safety and continued station operations. The station community is especially station operations. The station community is especially station operations. The station community is especially proud that, as a consequence of its rigorous development proud that, as a consequence of its rigorous development proud that, as a consequence of its rigorous development methodology, ISS software quality is world class, achieving methodology, ISS software quality is world class, achieving methodology, ISS software quality is world class, achieving a 6 sigma error-free standard. a 6 sigma error-free standard. a 6 sigma error-free standard.

The success of this endeavor can be attributed to a num- The success of this endeavor can be attributed to a num- The success of this endeavor can be attributed to a num- ber of factors, not the least of which is the dedication and ber of factors, not the least of which is the dedication and ber of factors, not the least of which is the dedication and hard work of professionals around the world who share a hard work of professionals around the world who share a hard work of professionals around the world who share a passion for spaceflight and exploration. A more practical passion for spaceflight and exploration. A more practical passion for spaceflight and exploration. A more practical reason, though, is the carefully considered architecture, reason, though, is the carefully considered architecture, reason, though, is the carefully considered architecture, and development methodology, which allowed each of and development methodology, which allowed each of and development methodology, which allowed each of the partner elements to come online over a span of years. the partner elements to come online over a span of years. the partner elements to come online over a span of years. Building a functioning space station is a bit like having to Building a functioning space station is a bit like having to Building a functioning space station is a bit like having to construct a giant industrial facility over a 10- or 15-year pe- construct a giant industrial facility over a 10- or 15-year pe- construct a giant industrial facility over a 10- or 15-year pe- riod, without ever having the benefit to integrate and test all riod, without ever having the benefit to integrate and test all riod, without ever having the benefit to integrate and test all the pieces together until each piece individually becomes the pieces together until each piece individually becomes the pieces together until each piece individually becomes operational. It was a robust computing architecture, and a operational. It was a robust computing architecture, and a operational. It was a robust computing architecture, and a world-class testing facility in Houston, that allowed those world-class testing facility in Houston, that allowed those world-class testing facility in Houston, that allowed those passionate professionals to be successful. passionate professionals to be successful. passionate professionals to be successful.

Breathing on the ISS Breathing on the ISS Breathing on the ISS

Life support systems on the ISS must not only supply Life support systems on the ISS must not only supply Life support systems on the ISS must not only supply oxygen and remove carbon dioxide from the cabin’s oxygen and remove carbon dioxide from the cabin’s oxygen and remove carbon dioxide from the cabin’s atmosphere but also prevent gases like ammonia and atmosphere but also prevent gases like ammonia and atmosphere but also prevent gases like ammonia and acetone, which astronauts emit themselves in small acetone, which astronauts emit themselves in small acetone, which astronauts emit themselves in small quantities, from accumulating. Vaporous chemicals from quantities, from accumulating. Vaporous chemicals from quantities, from accumulating. Vaporous chemicals from equipment offgassing and science experiments are a equipment offgassing and science experiments are a equipment offgassing and science experiments are a potential hazard, too, if they combine in unforeseen ways potential hazard, too, if they combine in unforeseen ways potential hazard, too, if they combine in unforeseen ways with other elements in the air supply. So while air in space with other elements in the air supply. So while air in space with other elements in the air supply. So while air in space

B-51 B-51 B-51 is undeniably rare, managing it is no small problem. To is undeniably rare, managing it is no small problem. To is undeniably rare, managing it is no small problem. To ensure the safety of the crew, the ISS has redundant sup- ensure the safety of the crew, the ISS has redundant sup- ensure the safety of the crew, the ISS has redundant sup- plies of that essential gas—oxygen. Most of the station’s plies of that essential gas—oxygen. Most of the station’s plies of that essential gas—oxygen. Most of the station’s oxygen comes from a process called “electrolysis,” which oxygen comes from a process called “electrolysis,” which oxygen comes from a process called “electrolysis,” which uses electricity from the ISS solar panels that powers a uses electricity from the ISS solar panels that powers a uses electricity from the ISS solar panels that powers a device to split water into oxygen and hydrogen gases. device to split water into oxygen and hydrogen gases. device to split water into oxygen and hydrogen gases. Each molecule of water contains two hydrogen atoms and Each molecule of water contains two hydrogen atoms and Each molecule of water contains two hydrogen atoms and one oxygen atom. Running a current through water causes one oxygen atom. Running a current through water causes one oxygen atom. Running a current through water causes these atoms to separate and recombine as gaseous these atoms to separate and recombine as gaseous these atoms to separate and recombine as gaseous oxygen (O2) and hydrogen (H2). The oxygen that people oxygen (O2) and hydrogen (H2). The oxygen that people oxygen (O2) and hydrogen (H2). The oxygen that people breathe on Earth also comes from the splitting of water, but breathe on Earth also comes from the splitting of water, but breathe on Earth also comes from the splitting of water, but it is not a mechanical process. Plants, algae, cyanobac- it is not a mechanical process. Plants, algae, cyanobac- it is not a mechanical process. Plants, algae, cyanobac- teria, and phytoplankton all split water molecules as part teria, and phytoplankton all split water molecules as part teria, and phytoplankton all split water molecules as part of photosynthesis—the process that converts sunlight, of photosynthesis—the process that converts sunlight, of photosynthesis—the process that converts sunlight, carbon dioxide, and water into sugars for food. Oxygen carbon dioxide, and water into sugars for food. Oxygen carbon dioxide, and water into sugars for food. Oxygen is a byproduct of this process and is released into the is a byproduct of this process and is released into the is a byproduct of this process and is released into the atmosphere. Eventually, it would be great if plants could atmosphere. Eventually, it would be great if plants could atmosphere. Eventually, it would be great if plants could be used to produce oxygen for the station. However, the be used to produce oxygen for the station. However, the be used to produce oxygen for the station. However, the chemical-mechanical systems are much more compact, chemical-mechanical systems are much more compact, chemical-mechanical systems are much more compact, less labor intensive, and more reliable than a plant-based less labor intensive, and more reliable than a plant-based less labor intensive, and more reliable than a plant-based system. A plant-based life support system design is pres- system. A plant-based life support system design is pres- system. A plant-based life support system design is pres- ently at the basic research and demonstration stage of ently at the basic research and demonstration stage of ently at the basic research and demonstration stage of maturity, and there are myriad challenges that must be maturity, and there are myriad challenges that must be maturity, and there are myriad challenges that must be overcome to make it viable. overcome to make it viable. overcome to make it viable.

Hydrogen that is left over from splitting water will be Hydrogen that is left over from splitting water will be Hydrogen that is left over from splitting water will be vented into space, at least at first. The space station’s vented into space, at least at first. The space station’s vented into space, at least at first. The space station’s Environmental Control and Life Support System (ECLS) Environmental Control and Life Support System (ECLS) Environmental Control and Life Support System (ECLS) includes a machine that combines hydrogen with excess includes a machine that combines hydrogen with excess includes a machine that combines hydrogen with excess carbon dioxide from the air in a chemical reaction that carbon dioxide from the air in a chemical reaction that carbon dioxide from the air in a chemical reaction that produces water and methane. This water helps replace the produces water and methane. This water helps replace the produces water and methane. This water helps replace the water used to make oxygen, and methane is vented into water used to make oxygen, and methane is vented into water used to make oxygen, and methane is vented into space. Various uses for methane are being considered, space. Various uses for methane are being considered, space. Various uses for methane are being considered, including expelling it to help provide the thrust necessary including expelling it to help provide the thrust necessary including expelling it to help provide the thrust necessary to maintain the ISS orbit. At present, all of the venting that to maintain the ISS orbit. At present, all of the venting that to maintain the ISS orbit. At present, all of the venting that goes overboard is designed to be nonpropulsive to avoid goes overboard is designed to be nonpropulsive to avoid goes overboard is designed to be nonpropulsive to avoid disturbing the station’s attitude. disturbing the station’s attitude. disturbing the station’s attitude.

The ISS also has large tanks of compressed oxygen and The ISS also has large tanks of compressed oxygen and The ISS also has large tanks of compressed oxygen and nitrogen mounted on the outside of the airlock module. nitrogen mounted on the outside of the airlock module. nitrogen mounted on the outside of the airlock module. These tanks serve as the primary supply of oxygen for the These tanks serve as the primary supply of oxygen for the These tanks serve as the primary supply of oxygen for the U.S. spacesuits and backup oxygen for the crew. U.S. spacesuits and backup oxygen for the crew. U.S. spacesuits and backup oxygen for the crew.

Another source of oxygen can come from “perchlorate Another source of oxygen can come from “perchlorate Another source of oxygen can come from “perchlorate candles,” which produce O2 via chemical reactions inside candles,” which produce O2 via chemical reactions inside candles,” which produce O2 via chemical reactions inside a metal canister. A “perchlorate candle” is a metal canister a metal canister. A “perchlorate candle” is a metal canister a metal canister. A “perchlorate candle” is a metal canister with perchlorate packed inside it. A canister has an igniter with perchlorate packed inside it. A canister has an igniter with perchlorate packed inside it. A canister has an igniter pin. When this pin is struck, the reaction starts. Perchlorate pin. When this pin is struck, the reaction starts. Perchlorate pin. When this pin is struck, the reaction starts. Perchlorate continues to burn until it is all used. Each canister releases continues to burn until it is all used. Each canister releases continues to burn until it is all used. Each canister releases enough oxygen for one person for one day. enough oxygen for one person for one day. enough oxygen for one person for one day.

The air in the space station is kept in constant motion, and The air in the space station is kept in constant motion, and The air in the space station is kept in constant motion, and all the air passes through filters—called High-Efficiency all the air passes through filters—called High-Efficiency all the air passes through filters—called High-Efficiency Particle Air (HEPA) filters—on its way to the temperature Particle Air (HEPA) filters—on its way to the temperature Particle Air (HEPA) filters—on its way to the temperature and humidity control systems. The filters were originally and humidity control systems. The filters were originally and humidity control systems. The filters were originally designed to remove particulates, and they are very good designed to remove particulates, and they are very good designed to remove particulates, and they are very good at removing small particles and microbes. Microbes can at removing small particles and microbes. Microbes can at removing small particles and microbes. Microbes can

B-52 B-52 B-52 ride in the air on particles of dust or in tiny clumps of fungi. ride in the air on particles of dust or in tiny clumps of fungi. ride in the air on particles of dust or in tiny clumps of fungi. The humidity of the air in the station is maintained at 65 The humidity of the air in the station is maintained at 65 The humidity of the air in the station is maintained at 65 to 70 percent. Controlling the humidity is an effective way to 70 percent. Controlling the humidity is an effective way to 70 percent. Controlling the humidity is an effective way of discouraging microbe growth, and the temperature is of discouraging microbe growth, and the temperature is of discouraging microbe growth, and the temperature is a fairly constant 72ºF on board. a fairly constant 72ºF on board. a fairly constant 72ºF on board.

Water on the ISS Water on the ISS Water on the ISS

Rationing and recycling is an essential part of daily life Rationing and recycling is an essential part of daily life Rationing and recycling is an essential part of daily life on the ISS. In orbit, where Earth’s natural life support is on the ISS. In orbit, where Earth’s natural life support is on the ISS. In orbit, where Earth’s natural life support is missing, the space station itself has to constantly provide missing, the space station itself has to constantly provide missing, the space station itself has to constantly provide abundant power, clean water, and breathable air at the abundant power, clean water, and breathable air at the abundant power, clean water, and breathable air at the right temperature and humidity. The space station’s ECLS right temperature and humidity. The space station’s ECLS right temperature and humidity. The space station’s ECLS helps astronauts use and reuse their precious supplies of helps astronauts use and reuse their precious supplies of helps astronauts use and reuse their precious supplies of water. This regenerative system can recycle almost every water. This regenerative system can recycle almost every water. This regenerative system can recycle almost every drop of water on the station and support a crew of six with drop of water on the station and support a crew of six with drop of water on the station and support a crew of six with minimal resupplies. minimal resupplies. minimal resupplies.

The ECLS Water Recovery System (WRS) reclaims waste The ECLS Water Recovery System (WRS) reclaims waste The ECLS Water Recovery System (WRS) reclaims waste waters from the station’s humidity condensate, from urine waters from the station’s humidity condensate, from urine waters from the station’s humidity condensate, from urine and flush water, and from oral hygiene and hand washing. and flush water, and from oral hygiene and hand washing. and flush water, and from oral hygiene and hand washing. Without such careful recycling, 40,000 pounds of water Without such careful recycling, 40,000 pounds of water Without such careful recycling, 40,000 pounds of water per year from the Earth would be required to resupply a per year from the Earth would be required to resupply a per year from the Earth would be required to resupply a minimum of four crew members to live on the station, but minimum of four crew members to live on the station, but minimum of four crew members to live on the station, but it is very expensive to ferry water from Earth. it is very expensive to ferry water from Earth. it is very expensive to ferry water from Earth.

Water leaving the space station’s purification machines is Water leaving the space station’s purification machines is Water leaving the space station’s purification machines is cleaner than what most of us drink on Earth. The station’s cleaner than what most of us drink on Earth. The station’s cleaner than what most of us drink on Earth. The station’s water is practically ultra-pure by the time the water’s puri- water is practically ultra-pure by the time the water’s puri- water is practically ultra-pure by the time the water’s puri- fication process is finished, and the reason is that the ISS fication process is finished, and the reason is that the ISS fication process is finished, and the reason is that the ISS has a much more aggressive water treatment process than has a much more aggressive water treatment process than has a much more aggressive water treatment process than municipal wastewater treatment plants. The water purifica- municipal wastewater treatment plants. The water purifica- municipal wastewater treatment plants. The water purifica- tion machines on the ISS cleanse wastewater in a four-step tion machines on the ISS cleanse wastewater in a four-step tion machines on the ISS cleanse wastewater in a four-step process. The first step is a filter that removes particles and process. The first step is a filter that removes particles and process. The first step is a filter that removes particles and debris. Then the water passes through the “multifiltration debris. Then the water passes through the “multifiltration debris. Then the water passes through the “multifiltration beds,” which contain substances that remove organic and beds,” which contain substances that remove organic and beds,” which contain substances that remove organic and inorganic impurities. After that, the “catalytic oxidation inorganic impurities. After that, the “catalytic oxidation inorganic impurities. After that, the “catalytic oxidation reactor” removes volatile organic compounds and kills reactor” removes volatile organic compounds and kills reactor” removes volatile organic compounds and kills bacteria and viruses by heating the water to as much as bacteria and viruses by heating the water to as much as bacteria and viruses by heating the water to as much as 265ºF. And finally, the water is treated with iodine. As a 265ºF. And finally, the water is treated with iodine. As a 265ºF. And finally, the water is treated with iodine. As a result of such disinfection, there should be fewer than 100 result of such disinfection, there should be fewer than 100 result of such disinfection, there should be fewer than 100 microbes in 100 milliliters of water. microbes in 100 milliliters of water. microbes in 100 milliliters of water.

Once the water is purified, astronauts do everything pos- Once the water is purified, astronauts do everything pos- Once the water is purified, astronauts do everything pos- sible to use it efficiently. On the ground, people flick on the sible to use it efficiently. On the ground, people flick on the sible to use it efficiently. On the ground, people flick on the faucet, and they probably waste a couple of liters of water faucet, and they probably waste a couple of liters of water faucet, and they probably waste a couple of liters of water just because it is free and the water pressure is high. On just because it is free and the water pressure is high. On just because it is free and the water pressure is high. On the ISS, the water pressure is about half what we might the ISS, the water pressure is about half what we might the ISS, the water pressure is about half what we might experience in a typical household. Astronauts do not use experience in a typical household. Astronauts do not use experience in a typical household. Astronauts do not use faucets on the ISS; they use a washcloth. It is much more faucets on the ISS; they use a washcloth. It is much more faucets on the ISS; they use a washcloth. It is much more efficient. If you are an astronaut, you will wet the washcloth efficient. If you are an astronaut, you will wet the washcloth efficient. If you are an astronaut, you will wet the washcloth with a spray nozzle and then use the cloth to wash your with a spray nozzle and then use the cloth to wash your with a spray nozzle and then use the cloth to wash your hands. On the space station, astronauts wash their hands hands. On the space station, astronauts wash their hands hands. On the space station, astronauts wash their hands with less than one-tenth of the water that people normally with less than one-tenth of the water that people normally with less than one-tenth of the water that people normally use on Earth. Instead of consuming 50 liters of water to use on Earth. Instead of consuming 50 liters of water to use on Earth. Instead of consuming 50 liters of water to take a shower, which is typical on Earth, astronauts on the take a shower, which is typical on Earth, astronauts on the take a shower, which is typical on Earth, astronauts on the ISS use less than 4 liters to bathe. ISS use less than 4 liters to bathe. ISS use less than 4 liters to bathe.

B-53 B-53 B-53 However, even with intense conservation and recycling However, even with intense conservation and recycling However, even with intense conservation and recycling efforts, the station gradually loses water because of inef- efforts, the station gradually loses water because of inef- efforts, the station gradually loses water because of inef- ficiencies in the life support system. The station will always ficiencies in the life support system. The station will always ficiencies in the life support system. The station will always need resupply because none of the water reprocessing need resupply because none of the water reprocessing need resupply because none of the water reprocessing technology that is available right now for space flight is technology that is available right now for space flight is technology that is available right now for space flight is 100 percent efficient, and there is always some loss. Lost 100 percent efficient, and there is always some loss. Lost 100 percent efficient, and there is always some loss. Lost water is replaced by carrying it over from the space shuttle water is replaced by carrying it over from the space shuttle water is replaced by carrying it over from the space shuttle or from the Russian Progress unmanned resupply vehicle. or from the Russian Progress unmanned resupply vehicle. or from the Russian Progress unmanned resupply vehicle. The shuttle produces water as its fuel cells combine hy- The shuttle produces water as its fuel cells combine hy- The shuttle produces water as its fuel cells combine hy- drogen and oxygen to create electricity, and the Progress drogen and oxygen to create electricity, and the Progress drogen and oxygen to create electricity, and the Progress can be outfitted to carry large containers of water. can be outfitted to carry large containers of water. can be outfitted to carry large containers of water.

NASA scientists continue to look for ways to improve the NASA scientists continue to look for ways to improve the NASA scientists continue to look for ways to improve the life support systems of the ISS, reducing water losses and life support systems of the ISS, reducing water losses and life support systems of the ISS, reducing water losses and finding ways to reuse other waste products. If the water finding ways to reuse other waste products. If the water finding ways to reuse other waste products. If the water recycling systems can be improved to an efficiency of recycling systems can be improved to an efficiency of recycling systems can be improved to an efficiency of greater than about 95 percent, then the water contained in greater than about 95 percent, then the water contained in greater than about 95 percent, then the water contained in the station’s food supply would be enough to replace the the station’s food supply would be enough to replace the the station’s food supply would be enough to replace the lost water. This is the next generation of water processing lost water. This is the next generation of water processing lost water. This is the next generation of water processing systems. They are being developed now, but they are not systems. They are being developed now, but they are not systems. They are being developed now, but they are not ready for space flight yet. ready for space flight yet. ready for space flight yet.

Housekeeping on the ISS Housekeeping on the ISS Housekeeping on the ISS

Living in space is a daring adventure, but somebody still Living in space is a daring adventure, but somebody still Living in space is a daring adventure, but somebody still has to cook dinner and take out the trash. What does the has to cook dinner and take out the trash. What does the has to cook dinner and take out the trash. What does the ISS crew eat, and how is it cooked? All food is delivered ISS crew eat, and how is it cooked? All food is delivered ISS crew eat, and how is it cooked? All food is delivered by the U.S. space shuttle or the Russian Progress vehicle, by the U.S. space shuttle or the Russian Progress vehicle, by the U.S. space shuttle or the Russian Progress vehicle, the new European Automated Transfer Vehicle (ATV), or the new European Automated Transfer Vehicle (ATV), or the new European Automated Transfer Vehicle (ATV), or Japanese HII Transfer Vehicle (HTV). The crew helps se- Japanese HII Transfer Vehicle (HTV). The crew helps se- Japanese HII Transfer Vehicle (HTV). The crew helps se- lect the foods they want from a wide-ranging menu. Food lect the foods they want from a wide-ranging menu. Food lect the foods they want from a wide-ranging menu. Food aboard the space station comes in several forms. Most of aboard the space station comes in several forms. Most of aboard the space station comes in several forms. Most of the food is processed and packaged in pouches or cans. the food is processed and packaged in pouches or cans. the food is processed and packaged in pouches or cans. Some food is dehydrated, and the astronauts add hot water Some food is dehydrated, and the astronauts add hot water Some food is dehydrated, and the astronauts add hot water and eat. A small amount is fresh food that includes fruits and eat. A small amount is fresh food that includes fruits and eat. A small amount is fresh food that includes fruits and vegetables but nothing that requires refrigeration. All and vegetables but nothing that requires refrigeration. All and vegetables but nothing that requires refrigeration. All food is stored at room temperature. food is stored at room temperature. food is stored at room temperature.

Water recycling efficiencies of greater than 95 percent are Water recycling efficiencies of greater than 95 percent are Water recycling efficiencies of greater than 95 percent are the goal. But other wastes cannot be recycled so efficiently, the goal. But other wastes cannot be recycled so efficiently, the goal. But other wastes cannot be recycled so efficiently, particularly solid waste from food containers, experiments, particularly solid waste from food containers, experiments, particularly solid waste from food containers, experiments, empty equipment containers, and other ISS activities. So: empty equipment containers, and other ISS activities. So: empty equipment containers, and other ISS activities. So: Who takes out the trash? Again, Progress and the space Who takes out the trash? Again, Progress and the space Who takes out the trash? Again, Progress and the space shuttle come to the rescue. Every arrival of the shuttle shuttle come to the rescue. Every arrival of the shuttle shuttle come to the rescue. Every arrival of the shuttle brings fresh supplies. And when it leaves, it becomes the brings fresh supplies. And when it leaves, it becomes the brings fresh supplies. And when it leaves, it becomes the world’s most expensive trash hauler. Bags and containers world’s most expensive trash hauler. Bags and containers world’s most expensive trash hauler. Bags and containers of sealed trash are brought back to Earth. More exciting, of sealed trash are brought back to Earth. More exciting, of sealed trash are brought back to Earth. More exciting, perhaps, is how the Russian Progress disposes of trash. perhaps, is how the Russian Progress disposes of trash. perhaps, is how the Russian Progress disposes of trash. Again, when it arrives, it brings fresh supplies (but no Again, when it arrives, it brings fresh supplies (but no Again, when it arrives, it brings fresh supplies (but no crews, since it is just a supply vehicle). And when the crews, since it is just a supply vehicle). And when the crews, since it is just a supply vehicle). And when the fresh supplies are unloaded, the trash bags are piled in, fresh supplies are unloaded, the trash bags are piled in, fresh supplies are unloaded, the trash bags are piled in, and the Progress is sealed. After it disconnects from the and the Progress is sealed. After it disconnects from the and the Progress is sealed. After it disconnects from the ISS, it is placed into a lower orbit and makes a controlled ISS, it is placed into a lower orbit and makes a controlled ISS, it is placed into a lower orbit and makes a controlled reentry during which it and the trash are incinerated over reentry during which it and the trash are incinerated over reentry during which it and the trash are incinerated over the ocean. The same is true for the new ATV and HTV the ocean. The same is true for the new ATV and HTV the ocean. The same is true for the new ATV and HTV resupply vehicles now in use. resupply vehicles now in use. resupply vehicles now in use.

B-54 B-54 B-54 Relaxation and Recreation on the ISS Relaxation and Recreation on the ISS Relaxation and Recreation on the ISS

Crews are always busy during their tours of duty on the Crews are always busy during their tours of duty on the Crews are always busy during their tours of duty on the ISS. Nevertheless, relaxation and recreation for the men ISS. Nevertheless, relaxation and recreation for the men ISS. Nevertheless, relaxation and recreation for the men and women living aboard the space station play a very and women living aboard the space station play a very and women living aboard the space station play a very important role. A significant portion of nonworking time is important role. A significant portion of nonworking time is important role. A significant portion of nonworking time is taken up in a stiff regimen of exercise and physical activity taken up in a stiff regimen of exercise and physical activity taken up in a stiff regimen of exercise and physical activity by using a bicycle, rowing machine, treadmill, and various by using a bicycle, rowing machine, treadmill, and various by using a bicycle, rowing machine, treadmill, and various other equipment. Data from the ISS and other previous other equipment. Data from the ISS and other previous other equipment. Data from the ISS and other previous long-duration flights show that significant physical deg- long-duration flights show that significant physical deg- long-duration flights show that significant physical deg- radation of the human body occurs in space. The human radation of the human body occurs in space. The human radation of the human body occurs in space. The human body was really designed to function in a one-G gravita- body was really designed to function in a one-G gravita- body was really designed to function in a one-G gravita- tional field. Fluid loss, loss of muscle tissue, loss of bone tional field. Fluid loss, loss of muscle tissue, loss of bone tional field. Fluid loss, loss of muscle tissue, loss of bone mass, and changes in cardiovascular system and other mass, and changes in cardiovascular system and other mass, and changes in cardiovascular system and other organs all take place in zero-G. And the longer people organs all take place in zero-G. And the longer people organs all take place in zero-G. And the longer people stay there, the more significant the changes become. stay there, the more significant the changes become. stay there, the more significant the changes become. However, the good news is that the changes are reversible However, the good news is that the changes are reversible However, the good news is that the changes are reversible after return to Earth, and an active program of strenuous after return to Earth, and an active program of strenuous after return to Earth, and an active program of strenuous exercise in space can reduce these changes. exercise in space can reduce these changes. exercise in space can reduce these changes.

But what are the individual crew members doing when But what are the individual crew members doing when But what are the individual crew members doing when they are not working, exercising, or sleeping? Astronauts they are not working, exercising, or sleeping? Astronauts they are not working, exercising, or sleeping? Astronauts like to have fun, too. For space workers who stay on the like to have fun, too. For space workers who stay on the like to have fun, too. For space workers who stay on the ISS for many months, fun is an essential ingredient to the ISS for many months, fun is an essential ingredient to the ISS for many months, fun is an essential ingredient to the quality of their lives. Astronauts can take a certain amount quality of their lives. Astronauts can take a certain amount quality of their lives. Astronauts can take a certain amount of personal gear up with them. Things like checkers or of personal gear up with them. Things like checkers or of personal gear up with them. Things like checkers or chess sets, CDs and MP3 players, and similar items are chess sets, CDs and MP3 players, and similar items are chess sets, CDs and MP3 players, and similar items are allowed. Crew members can listen to their favorite music allowed. Crew members can listen to their favorite music allowed. Crew members can listen to their favorite music or watch DVD movies. A popular pastime while orbiting the or watch DVD movies. A popular pastime while orbiting the or watch DVD movies. A popular pastime while orbiting the Earth is simply looking out the window, and the ISS has Earth is simply looking out the window, and the ISS has Earth is simply looking out the window, and the ISS has numerous windows. Photography is a popular pastime. numerous windows. Photography is a popular pastime. numerous windows. Photography is a popular pastime. Astronauts often comment on their fascination and awe as Astronauts often comment on their fascination and awe as Astronauts often comment on their fascination and awe as they look at the Earth spin beneath them with its multiple they look at the Earth spin beneath them with its multiple they look at the Earth spin beneath them with its multiple shades and textures, and the spectacular sunsets and shades and textures, and the spectacular sunsets and shades and textures, and the spectacular sunsets and sunrises, occurring every 45 minutes above the Earth’s sunrises, occurring every 45 minutes above the Earth’s sunrises, occurring every 45 minutes above the Earth’s atmosphere. atmosphere. atmosphere.

B-55 B-55 B-55 Russian Soyuz Spacecraft Russian Soyuz Spacecraft Russian Soyuz Spacecraft

The Russian Soyuz has been a long-lived, adaptable, The Russian Soyuz has been a long-lived, adaptable, The Russian Soyuz has been a long-lived, adaptable, and highly successful crewed spacecraft design. The and highly successful crewed spacecraft design. The and highly successful crewed spacecraft design. The Soyuz first flew in 1967 and has flown more than 100 Soyuz first flew in 1967 and has flown more than 100 Soyuz first flew in 1967 and has flown more than 100 flights. Versions have been developed for a wide variety of flights. Versions have been developed for a wide variety of flights. Versions have been developed for a wide variety of missions—Earth orbit science, circumlunar, lunar orbital, missions—Earth orbit science, circumlunar, lunar orbital, missions—Earth orbit science, circumlunar, lunar orbital, military interceptors, light space stations, free-flying man- military interceptors, light space stations, free-flying man- military interceptors, light space stations, free-flying man- tended laboratories, space station crewed ferries, and tended laboratories, space station crewed ferries, and tended laboratories, space station crewed ferries, and space station logistics vehicles. space station logistics vehicles. space station logistics vehicles.

A Soyuz space capsule brought the first crew to the ISS in A Soyuz space capsule brought the first crew to the ISS in A Soyuz space capsule brought the first crew to the ISS in November 2000. Since that time, at least one Soyuz has November 2000. Since that time, at least one Soyuz has November 2000. Since that time, at least one Soyuz has always been at the station. The Soyuz TMA spacecraft is always been at the station. The Soyuz TMA spacecraft is always been at the station. The Soyuz TMA spacecraft is designed to serve as the ISS crew return vehicle, acting designed to serve as the ISS crew return vehicle, acting designed to serve as the ISS crew return vehicle, acting as a lifeboat in the event an emergency would require as a lifeboat in the event an emergency would require as a lifeboat in the event an emergency would require the crew to leave the station. A new Soyuz capsule is the crew to leave the station. A new Soyuz capsule is the crew to leave the station. A new Soyuz capsule is normally delivered to the station by a taxi crew every six normally delivered to the station by a taxi crew every six normally delivered to the station by a taxi crew every six months; the taxi crew then returns to Earth in the older months; the taxi crew then returns to Earth in the older months; the taxi crew then returns to Earth in the older Soyuz capsule. Soyuz capsule. Soyuz capsule.

The Soyuz spacecraft is launched to the ISS from the The Soyuz spacecraft is launched to the ISS from the The Soyuz spacecraft is launched to the ISS from the Baikonur Cosmodrome in Kazakhstan in central Asia. Baikonur Cosmodrome in Kazakhstan in central Asia. Baikonur Cosmodrome in Kazakhstan in central Asia. The Soyuz consists of an orbital module, which includes The Soyuz consists of an orbital module, which includes The Soyuz consists of an orbital module, which includes the docking mechanism; an instrumentation/propulsion the docking mechanism; an instrumentation/propulsion the docking mechanism; an instrumentation/propulsion module; and a descent module, which is the only portion module; and a descent module, which is the only portion module; and a descent module, which is the only portion of the Soyuz that survives the return to Earth. A Soyuz of the Soyuz that survives the return to Earth. A Soyuz of the Soyuz that survives the return to Earth. A Soyuz trip to the station takes two days from launch to docking, trip to the station takes two days from launch to docking, trip to the station takes two days from launch to docking, but the return to Earth takes less than 3.5 hours. The but the return to Earth takes less than 3.5 hours. The but the return to Earth takes less than 3.5 hours. The rendezvous and docking are both automated; however, rendezvous and docking are both automated; however, rendezvous and docking are both automated; however, the Soyuz crew has the capability to manually intervene the Soyuz crew has the capability to manually intervene the Soyuz crew has the capability to manually intervene or execute these operations. or execute these operations. or execute these operations.

As many as three crew members can launch and return to As many as three crew members can launch and return to As many as three crew members can launch and return to Earth from the station aboard a Soyuz TMA spacecraft. The Earth from the station aboard a Soyuz TMA spacecraft. The Earth from the station aboard a Soyuz TMA spacecraft. The vehicle lands on the flat steppes of Kazakhstan. vehicle lands on the flat steppes of Kazakhstan. vehicle lands on the flat steppes of Kazakhstan.

A Soyuz spacecraft departs from the ISS, carrying a taxi A Soyuz spacecraft departs from the ISS, carrying a taxi A Soyuz spacecraft departs from the ISS, carrying a taxi crew. crew. crew.

B-56 B-56 B-56 Progress Spacecraft Progress Spacecraft Progress Spacecraft

The Progress resupply vehicle is an automated, unpiloted The Progress resupply vehicle is an automated, unpiloted The Progress resupply vehicle is an automated, unpiloted version of the Soyuz spacecraft and is used to bring sup- version of the Soyuz spacecraft and is used to bring sup- version of the Soyuz spacecraft and is used to bring sup- plies and fuel to the ISS. The Progress also has the ability plies and fuel to the ISS. The Progress also has the ability plies and fuel to the ISS. The Progress also has the ability to raise the station’s altitude and control the orientation of to raise the station’s altitude and control the orientation of to raise the station’s altitude and control the orientation of the station using the vehicle’s thrusters. the station using the vehicle’s thrusters. the station using the vehicle’s thrusters.

Both the Progress M and M1 versions have a pressurized Both the Progress M and M1 versions have a pressurized Both the Progress M and M1 versions have a pressurized cargo module that can carry up to 3,748 lb (1,700 kg) of cargo module that can carry up to 3,748 lb (1,700 kg) of cargo module that can carry up to 3,748 lb (1,700 kg) of supplies, a refueling module with eight propellant tanks supplies, a refueling module with eight propellant tanks supplies, a refueling module with eight propellant tanks that can hold up to 3,836 lb (1,740 kg) of fuel, and an that can hold up to 3,836 lb (1,740 kg) of fuel, and an that can hold up to 3,836 lb (1,740 kg) of fuel, and an instrumentation/propulsion module where the Progress instrumentation/propulsion module where the Progress instrumentation/propulsion module where the Progress systems equipment and thrusters are located. systems equipment and thrusters are located. systems equipment and thrusters are located.

The Progress spacecraft is launched from the Baikonur The Progress spacecraft is launched from the Baikonur The Progress spacecraft is launched from the Baikonur Cosmodrome in Kazakhstan aboard a Soyuz rocket. It Cosmodrome in Kazakhstan aboard a Soyuz rocket. It Cosmodrome in Kazakhstan aboard a Soyuz rocket. It normally docks to the end of the station’s Zvezda service normally docks to the end of the station’s Zvezda service normally docks to the end of the station’s Zvezda service module, but it can also dock to the bottom of the Pirs Dock- module, but it can also dock to the bottom of the Pirs Dock- module, but it can also dock to the bottom of the Pirs Dock- ing Compartment. The rendezvous and docking are both ing Compartment. The rendezvous and docking are both ing Compartment. The rendezvous and docking are both automated; although once the spacecraft is within 492 ft automated; although once the spacecraft is within 492 ft automated; although once the spacecraft is within 492 ft (150 m) of the station, the Russian Mission Control Center (150 m) of the station, the Russian Mission Control Center (150 m) of the station, the Russian Mission Control Center just outside Moscow and the station crew monitor the ap- just outside Moscow and the station crew monitor the ap- just outside Moscow and the station crew monitor the ap- proach and docking. The Progress uses an automated, proach and docking. The Progress uses an automated, proach and docking. The Progress uses an automated, radar-based system called Kurs (Russian for “course”) to radar-based system called Kurs (Russian for “course”) to radar-based system called Kurs (Russian for “course”) to dock to the station. The station crew can also dock the dock to the station. The station crew can also dock the dock to the station. The station crew can also dock the Progress using the Telerobotically Operated Rendezvous Progress using the Telerobotically Operated Rendezvous Progress using the Telerobotically Operated Rendezvous Unit (TORU), a backup remote control docking system in Unit (TORU), a backup remote control docking system in Unit (TORU), a backup remote control docking system in the station’s Zvezda service module. the station’s Zvezda service module. the station’s Zvezda service module.

After the cargo is removed and before the Progress un- After the cargo is removed and before the Progress un- After the cargo is removed and before the Progress un- docks, the crew refills it with trash, unneeded equipment, docks, the crew refills it with trash, unneeded equipment, docks, the crew refills it with trash, unneeded equipment, and wastewater, which will burn up with the spacecraft and wastewater, which will burn up with the spacecraft and wastewater, which will burn up with the spacecraft when it re-enters the Earth’s atmosphere. when it re-enters the Earth’s atmosphere. when it re-enters the Earth’s atmosphere.

An unmanned Progress spacecraft is seen from the ISS An unmanned Progress spacecraft is seen from the ISS An unmanned Progress spacecraft is seen from the ISS following its undocking. following its undocking. following its undocking.

B-57 B-57 B-57 H-II Transfer Vehicle H-II Transfer Vehicle H-II Transfer Vehicle

The H-II Transfer Vehicle (HTV) is an expendable, un- The H-II Transfer Vehicle (HTV) is an expendable, un- The H-II Transfer Vehicle (HTV) is an expendable, un- manned resupply spacecraft developed by the Japan manned resupply spacecraft developed by the Japan manned resupply spacecraft developed by the Japan Aerospace Exploration Agency (JAXA) and its industrial Aerospace Exploration Agency (JAXA) and its industrial Aerospace Exploration Agency (JAXA) and its industrial team, led by Mitsubishi Heavy Industries. HTVs are de- team, led by Mitsubishi Heavy Industries. HTVs are de- team, led by Mitsubishi Heavy Industries. HTVs are de- signed to supply the ISS with supplies, payloads, and signed to supply the ISS with supplies, payloads, and signed to supply the ISS with supplies, payloads, and experiments. experiments. experiments.

Russian Progress vehicles and ESA’s ATV dock with the Russian Progress vehicles and ESA’s ATV dock with the Russian Progress vehicles and ESA’s ATV dock with the Russian segment of the ISS, which has smaller hatches Russian segment of the ISS, which has smaller hatches Russian segment of the ISS, which has smaller hatches than the U.S., European, and Japanese modules. Because than the U.S., European, and Japanese modules. Because than the U.S., European, and Japanese modules. Because the HTV is docked to one of these modules, it is designed the HTV is docked to one of these modules, it is designed the HTV is docked to one of these modules, it is designed with wider door openings that allow larger cargo to be with wider door openings that allow larger cargo to be with wider door openings that allow larger cargo to be moved into the station, giving the HTV the ability to bring moved into the station, giving the HTV the ability to bring moved into the station, giving the HTV the ability to bring with it large spare parts and science racks. with it large spare parts and science racks. with it large spare parts and science racks.

The Boeing ISS team in Huntsville, Ala., also worked with The Boeing ISS team in Huntsville, Ala., also worked with The Boeing ISS team in Huntsville, Ala., also worked with Mitsubishi Heavy Industries to design and assemble a Mitsubishi Heavy Industries to design and assemble a Mitsubishi Heavy Industries to design and assemble a passive common berthing mechanism (PCBM) used on passive common berthing mechanism (PCBM) used on passive common berthing mechanism (PCBM) used on the HTV that allows it to connect with the ISS. the HTV that allows it to connect with the ISS. the HTV that allows it to connect with the ISS.

Four main engines and 28 maneuvering jets fine-tune the Four main engines and 28 maneuvering jets fine-tune the Four main engines and 28 maneuvering jets fine-tune the HTV’s approach to the ISS. Fifty-seven solar panels affixed HTV’s approach to the ISS. Fifty-seven solar panels affixed HTV’s approach to the ISS. Fifty-seven solar panels affixed to the HTV’s exterior provide electricity for the craft. to the HTV’s exterior provide electricity for the craft. to the HTV’s exterior provide electricity for the craft.

The HTV does not have a complex docking-and-approach The HTV does not have a complex docking-and-approach The HTV does not have a complex docking-and-approach system. Instead, it is flown just close enough to the station system. Instead, it is flown just close enough to the station system. Instead, it is flown just close enough to the station to allow capture by Canadarm2, which pulls the HTV to a to allow capture by Canadarm2, which pulls the HTV to a to allow capture by Canadarm2, which pulls the HTV to a berthing port on the ISS Harmony module. berthing port on the ISS Harmony module. berthing port on the ISS Harmony module.

Backdropped by Earth, the unpiloted HTV-1 approaches Backdropped by Earth, the unpiloted HTV-1 approaches Backdropped by Earth, the unpiloted HTV-1 approaches the ISS. the ISS. the ISS.

HTVs can carry supplies in a combination of two different HTVs can carry supplies in a combination of two different HTVs can carry supplies in a combination of two different "segments" that can be attached together. The baseline "segments" that can be attached together. The baseline "segments" that can be attached together. The baseline configuration, known as the “Mixed Logistics Carrier,” uses configuration, known as the “Mixed Logistics Carrier,” uses configuration, known as the “Mixed Logistics Carrier,” uses one pressurized and one unpressurized segment and can one pressurized and one unpressurized segment and can one pressurized and one unpressurized segment and can carry 13,228 lb (6,000 kg) of cargo in total. HTV is the first carry 13,228 lb (6,000 kg) of cargo in total. HTV is the first carry 13,228 lb (6,000 kg) of cargo in total. HTV is the first unmanned vehicle that can carry both pressurized and unmanned vehicle that can carry both pressurized and unmanned vehicle that can carry both pressurized and unpressurized cargo. unpressurized cargo. unpressurized cargo.

B-58 B-58 B-58 Automated Transfer Vehicle (ATV) Automated Transfer Vehicle (ATV) Automated Transfer Vehicle (ATV) The ATV is an expendable, unmanned spacecraft devel- The ATV is an expendable, unmanned spacecraft devel- The ATV is an expendable, unmanned spacecraft devel- oped by the European Space Agency (ESA). ATVs are oped by the European Space Agency (ESA). ATVs are oped by the European Space Agency (ESA). ATVs are designed to supply the ISS with propellant, food, water, designed to supply the ISS with propellant, food, water, designed to supply the ISS with propellant, food, water, air, and payloads. In addition, ATVs can reboost the sta- air, and payloads. In addition, ATVs can reboost the sta- air, and payloads. In addition, ATVs can reboost the sta- tion into a higher orbit. ATVs use a GPS and star tracker tion into a higher orbit. ATVs use a GPS and star tracker tion into a higher orbit. ATVs use a GPS and star tracker to automatically rendezvous with the ISS. to automatically rendezvous with the ISS. to automatically rendezvous with the ISS. Like the Russian-built Progress, it carries cargo kept in a Like the Russian-built Progress, it carries cargo kept in a Like the Russian-built Progress, it carries cargo kept in a pressurized shirtsleeve environment so astronauts can pressurized shirtsleeve environment so astronauts can pressurized shirtsleeve environment so astronauts can have access to it without putting on a spacesuit. The ATV have access to it without putting on a spacesuit. The ATV have access to it without putting on a spacesuit. The ATV cargo section is based on the Italian-built MPLM. cargo section is based on the Italian-built MPLM. cargo section is based on the Italian-built MPLM. Height: 34 ft (10.3 m) Height: 34 ft (10.3 m) Height: 34 ft (10.3 m) Diameter: 15 ft (4.5 m) Diameter: 15 ft (4.5 m) Diameter: 15 ft (4.5 m) Cargo: 16,900 lb (7,667 kg) Cargo: 16,900 lb (7,667 kg) Cargo: 16,900 lb (7,667 kg) The first ATV, Jules Verne, was launched in March 2008 The first ATV, Jules Verne, was launched in March 2008 The first ATV, Jules Verne, was launched in March 2008 atop an Ariane 5ES from the equatorial ELA-3 launch site at atop an Ariane 5ES from the equatorial ELA-3 launch site at atop an Ariane 5ES from the equatorial ELA-3 launch site at the Guiana Space Centre. ATV-001 was named in memory the Guiana Space Centre. ATV-001 was named in memory the Guiana Space Centre. ATV-001 was named in memory of French science fiction writer Jules Verne and carried two of French science fiction writer Jules Verne and carried two of French science fiction writer Jules Verne and carried two of the author's original handwritten manuscripts and a 19th of the author's original handwritten manuscripts and a 19th of the author's original handwritten manuscripts and a 19th century illustrated edition of his novel, From the Earth to the century illustrated edition of his novel, From the Earth to the century illustrated edition of his novel, From the Earth to the Moon, to be received by the ISS crew as symbolic tokens Moon, to be received by the ISS crew as symbolic tokens Moon, to be received by the ISS crew as symbolic tokens of the success of the first flight. of the success of the first flight. of the success of the first flight.

The Jules Verne ATV approaches the ISS. The Jules Verne ATV approaches the ISS. The Jules Verne ATV approaches the ISS.

ATVs are intended to be launched every 17 months to ATVs are intended to be launched every 17 months to ATVs are intended to be launched every 17 months to resupply the ISS. ESA has already contracted suppliers resupply the ISS. ESA has already contracted suppliers resupply the ISS. ESA has already contracted suppliers to produce four more. ATV-002, named for German to produce four more. ATV-002, named for German to produce four more. ATV-002, named for German astronomer Johannes Kepler, is scheduled to be launched astronomer Johannes Kepler, is scheduled to be launched astronomer Johannes Kepler, is scheduled to be launched in November 2010. in November 2010. in November 2010. Once its mission is accomplished, the ATV, filled with as Once its mission is accomplished, the ATV, filled with as Once its mission is accomplished, the ATV, filled with as much as 14,000 lb of waste, separates. Its thrusters move the much as 14,000 lb of waste, separates. Its thrusters move the much as 14,000 lb of waste, separates. Its thrusters move the spacecraft out of orbit and place it on a flight path to perform spacecraft out of orbit and place it on a flight path to perform spacecraft out of orbit and place it on a flight path to perform a controlled destructive reentry. The Jules Verne burnt up a controlled destructive reentry. The Jules Verne burnt up a controlled destructive reentry. The Jules Verne burnt up on September 29, 2008, on entering the atmosphere above on September 29, 2008, on entering the atmosphere above on September 29, 2008, on entering the atmosphere above an uninhabited section of the Pacific Ocean. an uninhabited section of the Pacific Ocean. an uninhabited section of the Pacific Ocean. ATV missions are managed by a combined ESA/CNES ATV missions are managed by a combined ESA/CNES ATV missions are managed by a combined ESA/CNES (Centre National d’Études Spatiales) mission operations (Centre National d’Études Spatiales) mission operations (Centre National d’Études Spatiales) mission operations team based at ESA’s ATV Control Centre (ATV-CC) located team based at ESA’s ATV Control Centre (ATV-CC) located team based at ESA’s ATV Control Centre (ATV-CC) located at the Toulouse Space Centre (CST) in Toulouse, France. at the Toulouse Space Centre (CST) in Toulouse, France. at the Toulouse Space Centre (CST) in Toulouse, France.

B-59 B-59 B-59 The pressurized segment has a capacity of 9,921 lb The pressurized segment has a capacity of 9,921 lb The pressurized segment has a capacity of 9,921 lb (4,500 kg), which includes an optional docking adapter at (4,500 kg), which includes an optional docking adapter at (4,500 kg), which includes an optional docking adapter at one end to allow it to be unloaded in a shirtsleeve environ- one end to allow it to be unloaded in a shirtsleeve environ- one end to allow it to be unloaded in a shirtsleeve environ- ment. Pressurized supplies are stored in Cargo Transfer Bags ment. Pressurized supplies are stored in Cargo Transfer Bags ment. Pressurized supplies are stored in Cargo Transfer Bags (CTBs) loaded inside eight filing cabinet-sized International (CTBs) loaded inside eight filing cabinet-sized International (CTBs) loaded inside eight filing cabinet-sized International Standard Payload Racks (ISPRs) attached to the walls of Standard Payload Racks (ISPRs) attached to the walls of Standard Payload Racks (ISPRs) attached to the walls of the HTV. the HTV. the HTV.

The HTV is designed specifically to carry eight ISPRs in The HTV is designed specifically to carry eight ISPRs in The HTV is designed specifically to carry eight ISPRs in total. After the retirement of the space shuttle, the HTV total. After the retirement of the space shuttle, the HTV total. After the retirement of the space shuttle, the HTV will be the only vehicle that can carry ISPRs to the ISS. will be the only vehicle that can carry ISPRs to the ISS. will be the only vehicle that can carry ISPRs to the ISS. The HTV also has a tank to deliver up to 661 lb (300 kg) of The HTV also has a tank to deliver up to 661 lb (300 kg) of The HTV also has a tank to deliver up to 661 lb (300 kg) of water to the station. water to the station. water to the station.

The other hold is a lighter and slightly longer unpressur- The other hold is a lighter and slightly longer unpressur- The other hold is a lighter and slightly longer unpressur- ized segment with a capacity of 3,307 lb (1,500 kg), which ized segment with a capacity of 3,307 lb (1,500 kg), which ized segment with a capacity of 3,307 lb (1,500 kg), which includes a hatch on the side to allow it to be unloaded includes a hatch on the side to allow it to be unloaded includes a hatch on the side to allow it to be unloaded remotely. remotely. remotely. Length: 33 ft (10 m) Length: 33 ft (10 m) Length: 33 ft (10 m) Width: 14 ft (4.4 m) Width: 14 ft (4.4 m) Width: 14 ft (4.4 m) Weight: 21,000 lb (9,525 kg) Weight: 21,000 lb (9,525 kg) Weight: 21,000 lb (9,525 kg) The first mission, HTV-1, was launched on September The first mission, HTV-1, was launched on September The first mission, HTV-1, was launched on September 10, 2009, on an H-IIB launch vehicle from the Yoshinobu 10, 2009, on an H-IIB launch vehicle from the Yoshinobu 10, 2009, on an H-IIB launch vehicle from the Yoshinobu Launch Complex at the Tanegashima Space Center near the Launch Complex at the Tanegashima Space Center near the Launch Complex at the Tanegashima Space Center near the southernmost tip of Japan. The pressurized cargo consisted southernmost tip of Japan. The pressurized cargo consisted southernmost tip of Japan. The pressurized cargo consisted mainly of food, water, and clothing, while the unpressurized mainly of food, water, and clothing, while the unpressurized mainly of food, water, and clothing, while the unpressurized cargo contained two scientific experiments—Japan’s cargo contained two scientific experiments—Japan’s cargo contained two scientific experiments—Japan’s Superconducting Submillimeter-Wave Limb Emission Superconducting Submillimeter-Wave Limb Emission Superconducting Submillimeter-Wave Limb Emission Sounder (SMILES) and the U.S. Naval Research Labora- Sounder (SMILES) and the U.S. Naval Research Labora- Sounder (SMILES) and the U.S. Naval Research Labora- tory’s HICO-RAIDS Experiment Payload (HREP). Both were tory’s HICO-RAIDS Experiment Payload (HREP). Both were tory’s HICO-RAIDS Experiment Payload (HREP). Both were subsequently installed on Kibo’s Exposed Facility. subsequently installed on Kibo’s Exposed Facility. subsequently installed on Kibo’s Exposed Facility.

Six additional missions are planned, with HTV-2 scheduled Six additional missions are planned, with HTV-2 scheduled Six additional missions are planned, with HTV-2 scheduled for 2010. for 2010. for 2010.

Once its mission is complete, the HTV, filled with trash from Once its mission is complete, the HTV, filled with trash from Once its mission is complete, the HTV, filled with trash from the ISS to free up storage space, separates. Its thrusters the ISS to free up storage space, separates. Its thrusters the ISS to free up storage space, separates. Its thrusters move the spacecraft out of orbit and place it on a path to move the spacecraft out of orbit and place it on a path to move the spacecraft out of orbit and place it on a path to perform a controlled destructive reentry. HTV-1 burned up perform a controlled destructive reentry. HTV-1 burned up perform a controlled destructive reentry. HTV-1 burned up in the Earth’s atmosphere on November 2, 2009. in the Earth’s atmosphere on November 2, 2009. in the Earth’s atmosphere on November 2, 2009.

HTV missions are monitored and controlled by the HTV HTV missions are monitored and controlled by the HTV HTV missions are monitored and controlled by the HTV Mission Control Room (HTV MCR) at the Space Station Mission Control Room (HTV MCR) at the Space Station Mission Control Room (HTV MCR) at the Space Station Operations Facility (SSOF) in JAXA’s Tsukuba Space Operations Facility (SSOF) in JAXA’s Tsukuba Space Operations Facility (SSOF) in JAXA’s Tsukuba Space Center (TKSC) in collaboration with NASA’s Mission Control Center (TKSC) in collaboration with NASA’s Mission Control Center (TKSC) in collaboration with NASA’s Mission Control Center in Houston. Center in Houston. Center in Houston.

B-60 B-60 B-60 ISS Flights to Date ISS Flights to Date ISS Flights to Date 1A/R: Nov. 20, 1998 1A/R: Nov. 20, 1998 1A/R: Nov. 20, 1998 Launch Vehicle: Russian Proton rocket Launch Vehicle: Russian Proton rocket Launch Vehicle: Russian Proton rocket Elements: Zarya control module (Functional Elements: Zarya control module (Functional Elements: Zarya control module (Functional Cargo Block—FGB) Cargo Block—FGB) Cargo Block—FGB) Provided: Early propulsion, power, fuel Provided: Early propulsion, power, fuel Provided: Early propulsion, power, fuel storage, communications storage, communications storage, communications Current Duties: Passageway, stowage facility, Current Duties: Passageway, stowage facility, Current Duties: Passageway, stowage facility, docking port, fuel tank docking port, fuel tank docking port, fuel tank

2A/STS-88: Dec. 4, 1998 2A/STS-88: Dec. 4, 1998 2A/STS-88: Dec. 4, 1998 Launch Vehicle: Space shuttle Endeavour Launch Vehicle: Space shuttle Endeavour Launch Vehicle: Space shuttle Endeavour Elements: Node 1 "Unity"; two pressurized Elements: Node 1 "Unity"; two pressurized Elements: Node 1 "Unity"; two pressurized mating adapters mating adapters mating adapters Provided: Unity—connecting points for Z1 Provided: Unity—connecting points for Z1 Provided: Unity—connecting points for Z1 truss/U.S. Laboratory; PMA-1— truss/U.S. Laboratory; PMA-1— truss/U.S. Laboratory; PMA-1— connects U.S. and Russian ele- connects U.S. and Russian ele- connects U.S. and Russian ele- ments; PMA-2—shuttle docking ments; PMA-2—shuttle docking ments; PMA-2—shuttle docking location location location Future Duties: Connecting point for airlock, Future Duties: Connecting point for airlock, Future Duties: Connecting point for airlock, cupola, Node 3, Multi-Purpose cupola, Node 3, Multi-Purpose cupola, Node 3, Multi-Purpose Logistics Module, control module Logistics Module, control module Logistics Module, control module

2A.1/STS-96: May 27, 1999 2A.1/STS-96: May 27, 1999 2A.1/STS-96: May 27, 1999 Launch Vehicle: Space shuttle Discovery Launch Vehicle: Space shuttle Discovery Launch Vehicle: Space shuttle Discovery Elements: SPACEHAB; logistics flight Elements: SPACEHAB; logistics flight Elements: SPACEHAB; logistics flight Provided: Resupply cargo; external Russian Provided: Resupply cargo; external Russian Provided: Resupply cargo; external Russian cargo crane used for spacewalking cargo crane used for spacewalking cargo crane used for spacewalking maintenance activities maintenance activities maintenance activities

2A.2a/STS-101: May 19, 2000 2A.2a/STS-101: May 19, 2000 2A.2a/STS-101: May 19, 2000 Launch Vehicle: Space shuttle Atlantis Launch Vehicle: Space shuttle Atlantis Launch Vehicle: Space shuttle Atlantis Elements: SPACEHAB double cargo module Elements: SPACEHAB double cargo module Elements: SPACEHAB double cargo module Provided: Internal logistics and resupply Provided: Internal logistics and resupply Provided: Internal logistics and resupply cargo. Four of six batteries were cargo. Four of six batteries were cargo. Four of six batteries were swapped to restore the electrical swapped to restore the electrical swapped to restore the electrical power system to full redundancy power system to full redundancy power system to full redundancy

1R: July 12, 2000 1R: July 12, 2000 1R: July 12, 2000 Launch Vehicle: Russian Proton rocket Launch Vehicle: Russian Proton rocket Launch Vehicle: Russian Proton rocket Elements: Zvezda service module Elements: Zvezda service module Elements: Zvezda service module Provided: Early station living quarters, life Provided: Early station living quarters, life Provided: Early station living quarters, life support, propulsive attitude control support, propulsive attitude control support, propulsive attitude control and reboost capability; docking and reboost capability; docking and reboost capability; docking port for Progress-type cargo resup- port for Progress-type cargo resup- port for Progress-type cargo resup- ply vehicles and Soyuz vehicles ply vehicles and Soyuz vehicles ply vehicles and Soyuz vehicles

2A.2b/STS-106: Sept. 8, 2000 2A.2b/STS-106: Sept. 8, 2000 2A.2b/STS-106: Sept. 8, 2000 Launch Vehicle: Space shuttle Atlantis Launch Vehicle: Space shuttle Atlantis Launch Vehicle: Space shuttle Atlantis Elements: SPACEHAB double cargo module Elements: SPACEHAB double cargo module Elements: SPACEHAB double cargo module Provided: Unloaded supplies from Progress; Provided: Unloaded supplies from Progress; Provided: Unloaded supplies from Progress; battery and voltage converter instal- battery and voltage converter instal- battery and voltage converter instal- lation; connected power, data, and lation; connected power, data, and lation; connected power, data, and communications cables between communications cables between communications cables between the Zvezda and Zarya; installed the Zvezda and Zarya; installed the Zvezda and Zarya; installed treadmill; delivered toilet treadmill; delivered toilet treadmill; delivered toilet

B-61 B-61 B-61 3A/STS-92: Oct. 11, 2000 3A/STS-92: Oct. 11, 2000 3A/STS-92: Oct. 11, 2000 Launch Vehicle: Space shuttle Discovery Launch Vehicle: Space shuttle Discovery Launch Vehicle: Space shuttle Discovery Elements: Integrated truss structure (ITS) Elements: Integrated truss structure (ITS) Elements: Integrated truss structure (ITS) zenith 1 ( Z1), Pressurized Mating zenith 1 ( Z1), Pressurized Mating zenith 1 ( Z1), Pressurized Mating Adapter-3 (PMA), Ku-band commu- Adapter-3 (PMA), Ku-band commu- Adapter-3 (PMA), Ku-band commu- nications system, control moment nications system, control moment nications system, control moment gyros (CMGs) gyros (CMGs) gyros (CMGs) Provided: Z1 as early framework for first U.S. Provided: Z1 as early framework for first U.S. Provided: Z1 as early framework for first U.S. solar arrays (power); Ku-band solar arrays (power); Ku-band solar arrays (power); Ku-band communication system (science communication system (science communication system (science capability and U.S. television); capability and U.S. television); capability and U.S. television); nonpropulsive, electrically powered nonpropulsive, electrically powered nonpropulsive, electrically powered attitude control with CMG; PMA-3 attitude control with CMG; PMA-3 attitude control with CMG; PMA-3 provided shuttle docking port for provided shuttle docking port for provided shuttle docking port for solar array installation solar array installation solar array installation

2R: Oct. 31, 2000 2R: Oct. 31, 2000 2R: Oct. 31, 2000 Launch Vehicle: Russian Soyuz Launch Vehicle: Russian Soyuz Launch Vehicle: Russian Soyuz Elements: Expedition 1 Crew Elements: Expedition 1 Crew Elements: Expedition 1 Crew Established: First permanent human presence Established: First permanent human presence Established: First permanent human presence in space with three-person crew: in space with three-person crew: in space with three-person crew: commander Bill Shepherd, Soyuz commander Bill Shepherd, Soyuz commander Bill Shepherd, Soyuz commander Yuri Gidzenko, flight commander Yuri Gidzenko, flight commander Yuri Gidzenko, flight engineer Sergei Krikalev. Crew on engineer Sergei Krikalev. Crew on engineer Sergei Krikalev. Crew on board for 4 months; relieved by board for 4 months; relieved by board for 4 months; relieved by Expedition 2 crew on STS-102 Expedition 2 crew on STS-102 Expedition 2 crew on STS-102 Activities: Performed flight test, checked out Activities: Performed flight test, checked out Activities: Performed flight test, checked out communications systems, charged communications systems, charged communications systems, charged batteries for power tools, started batteries for power tools, started batteries for power tools, started water processors, activated life water processors, activated life water processors, activated life support systems, began scientific support systems, began scientific support systems, began scientific experiments experiments experiments

4A/STS-97: Nov. 30, 2000 4A/STS-97: Nov. 30, 2000 4A/STS-97: Nov. 30, 2000 Launch Vehicle: Space shuttle Endeavour Launch Vehicle: Space shuttle Endeavour Launch Vehicle: Space shuttle Endeavour Elements: Port 6 (P6) truss structure, photo- Elements: Port 6 (P6) truss structure, photo- Elements: Port 6 (P6) truss structure, photo- voltaic module, radiators voltaic module, radiators voltaic module, radiators Provided: First U.S. solar power with solar Provided: First U.S. solar power with solar Provided: First U.S. solar power with solar arrays and batteries (photovoltaic arrays and batteries (photovoltaic arrays and batteries (photovoltaic module), two radiators for early module), two radiators for early module), two radiators for early cooling, S-band communications cooling, S-band communications cooling, S-band communications system activated for voice and system activated for voice and system activated for voice and telemetry telemetry telemetry

5A/STS-98: Feb. 7, 2001 5A/STS-98: Feb. 7, 2001 5A/STS-98: Feb. 7, 2001 Launch Vehicle: Space shuttle Atlantis Launch Vehicle: Space shuttle Atlantis Launch Vehicle: Space shuttle Atlantis Elements: U.S. Laboratory “Destiny” Elements: U.S. Laboratory “Destiny” Elements: U.S. Laboratory “Destiny” Provided: Destiny is the centerpiece of ISS, Provided: Destiny is the centerpiece of ISS, Provided: Destiny is the centerpiece of ISS, where unprecedented science where unprecedented science where unprecedented science experiments will be performed. It experiments will be performed. It experiments will be performed. It contains five system racks and contains five system racks and contains five system racks and provides initial U.S. user capabil- provides initial U.S. user capabil- provides initial U.S. user capabil- ity. Control moment gyroscopes ity. Control moment gyroscopes ity. Control moment gyroscopes activated for electrically powered activated for electrically powered activated for electrically powered attitude control attitude control attitude control

B-62 B-62 B-62 5A.1/STS-102: March 8, 2001 5A.1/STS-102: March 8, 2001 5A.1/STS-102: March 8, 2001 Launch Vehicle: Space shuttle Discovery Launch Vehicle: Space shuttle Discovery Launch Vehicle: Space shuttle Discovery Elements: Leonardo Multi-Purpose Logistics Elements: Leonardo Multi-Purpose Logistics Elements: Leonardo Multi-Purpose Logistics Module (MPLM) carried equipment Module (MPLM) carried equipment Module (MPLM) carried equipment racks racks racks Provided: Logistics and resupply; pressurized Provided: Logistics and resupply; pressurized Provided: Logistics and resupply; pressurized MPLMs served as station’s “moving MPLMs served as station’s “moving MPLMs served as station’s “moving vans” and will carry new laboratory vans” and will carry new laboratory vans” and will carry new laboratory racks filled with equipment, experi- racks filled with equipment, experi- racks filled with equipment, experi- ments and supplies and return old ments and supplies and return old ments and supplies and return old racks and experiments to Earth racks and experiments to Earth racks and experiments to Earth Established: Second resident crew, Expedi- Established: Second resident crew, Expedi- Established: Second resident crew, Expedi- tion 2, to the station: commander tion 2, to the station: commander tion 2, to the station: commander Yury Usachev and flight engineers Yury Usachev and flight engineers Yury Usachev and flight engineers James Voss and Susan Helms. James Voss and Susan Helms. James Voss and Susan Helms. Returned Expedition 1 crew to Earth Returned Expedition 1 crew to Earth Returned Expedition 1 crew to Earth

6A/STS-100: April 19, 2001 6A/STS-100: April 19, 2001 6A/STS-100: April 19, 2001 Launch Vehicle: Space shuttle Endeavour Launch Vehicle: Space shuttle Endeavour Launch Vehicle: Space shuttle Endeavour Elements: Raffaello MPLM carried equipment Elements: Raffaello MPLM carried equipment Elements: Raffaello MPLM carried equipment racks; ultra-high frequency (UHF) racks; ultra-high frequency (UHF) racks; ultra-high frequency (UHF) antenna; Space Station Remote antenna; Space Station Remote antenna; Space Station Remote Manipulator System (SSRMS) Manipulator System (SSRMS) Manipulator System (SSRMS) Provided: Installation, activation and checkout Provided: Installation, activation and checkout Provided: Installation, activation and checkout of the SSRMS robotic arm of the SSRMS robotic arm of the SSRMS robotic arm (Canadarm2), which is critical to the (Canadarm2), which is critical to the (Canadarm2), which is critical to the continuing assembly of the ISS continuing assembly of the ISS continuing assembly of the ISS

7A/STS-104: July 12, 2001 7A/STS-104: July 12, 2001 7A/STS-104: July 12, 2001 Launch Vehicle: Space shuttle Atlantis Launch Vehicle: Space shuttle Atlantis Launch Vehicle: Space shuttle Atlantis Elements: Joint airlock “Quest”; high-pressure Elements: Joint airlock “Quest”; high-pressure Elements: Joint airlock “Quest”; high-pressure gas tanks (two oxygen and two gas tanks (two oxygen and two gas tanks (two oxygen and two nitrogen) installed on the airlock nitrogen) installed on the airlock nitrogen) installed on the airlock Provided: Installation, checkout and first use Provided: Installation, checkout and first use Provided: Installation, checkout and first use of the joint airlock, which will sup- of the joint airlock, which will sup- of the joint airlock, which will sup- port the use of either U.S. space- port the use of either U.S. space- port the use of either U.S. space- suits or Russian Orlan spacesuits suits or Russian Orlan spacesuits suits or Russian Orlan spacesuits during spacewalks during spacewalks during spacewalks

7A.1/STS-105: Aug. 14, 2001 7A.1/STS-105: Aug. 14, 2001 7A.1/STS-105: Aug. 14, 2001 Launch Vehicle: Space shuttle Discovery Launch Vehicle: Space shuttle Discovery Launch Vehicle: Space shuttle Discovery Elements: Leonardo MPLM carried equipment Elements: Leonardo MPLM carried equipment Elements: Leonardo MPLM carried equipment racks racks racks Provided: Logistics and resupply Provided: Logistics and resupply Provided: Logistics and resupply Established: Third resident crew, Expedition 3, Established: Third resident crew, Expedition 3, Established: Third resident crew, Expedition 3, to the station: commander Frank to the station: commander Frank to the station: commander Frank Culbertson and flight engineers Culbertson and flight engineers Culbertson and flight engineers Vladimir Dezhurov and Mikhail Vladimir Dezhurov and Mikhail Vladimir Dezhurov and Mikhail Tyurin. Returned Expedition 2 crew Tyurin. Returned Expedition 2 crew Tyurin. Returned Expedition 2 crew to Earth to Earth to Earth

B-63 B-63 B-63 UF-1/STS-108: Dec. 5, 2001 UF-1/STS-108: Dec. 5, 2001 UF-1/STS-108: Dec. 5, 2001 Launch Vehicle: Space shuttle Endeavour Launch Vehicle: Space shuttle Endeavour Launch Vehicle: Space shuttle Endeavour Elements: Raffaello MPLM carried equipment Elements: Raffaello MPLM carried equipment Elements: Raffaello MPLM carried equipment racks, STARSHINE 2 satellite racks, STARSHINE 2 satellite racks, STARSHINE 2 satellite Established: Fourth resident crew, Expedition Established: Fourth resident crew, Expedition Established: Fourth resident crew, Expedition 4, to the station: commander Yuri 4, to the station: commander Yuri 4, to the station: commander Yuri Onufrienko and flight engineers Onufrienko and flight engineers Onufrienko and flight engineers Daniel Bursch and Carl Walz. Daniel Bursch and Carl Walz. Daniel Bursch and Carl Walz. Returned Expedition 3 crew to Earth Returned Expedition 3 crew to Earth Returned Expedition 3 crew to Earth

8A/STS-110: April 8, 2002 8A/STS-110: April 8, 2002 8A/STS-110: April 8, 2002 Launch Vehicle: Space shuttle Atlantis Launch Vehicle: Space shuttle Atlantis Launch Vehicle: Space shuttle Atlantis Elements: Starboard 0 (S0) central integrated Elements: Starboard 0 (S0) central integrated Elements: Starboard 0 (S0) central integrated truss structure; mobile transporter, truss structure; mobile transporter, truss structure; mobile transporter, which was attached to the mobile which was attached to the mobile which was attached to the mobile base system during mission STS- base system during mission STS- base system during mission STS- 111 to create the first “railroad in 111 to create the first “railroad in 111 to create the first “railroad in space” space” space”

UF-2/STS-111: June 5, 2002 UF-2/STS-111: June 5, 2002 UF-2/STS-111: June 5, 2002 Launch Vehicle: Space shuttle Endeavour Launch Vehicle: Space shuttle Endeavour Launch Vehicle: Space shuttle Endeavour Elements: Leonardo MPLM carried equipment Elements: Leonardo MPLM carried equipment Elements: Leonardo MPLM carried equipment racks; mobile base system (MBS) racks; mobile base system (MBS) racks; mobile base system (MBS) Provided: Repaired wrist roll joint on Provided: Repaired wrist roll joint on Provided: Repaired wrist roll joint on Canadarm2; installed MBS to Canadarm2; installed MBS to Canadarm2; installed MBS to mobile transporter, previously deliv- mobile transporter, previously deliv- mobile transporter, previously deliv- ered on STS-110, which completed ered on STS-110, which completed ered on STS-110, which completed the Mobile Servicing System. The the Mobile Servicing System. The the Mobile Servicing System. The Mobile Servicing System will pro- Mobile Servicing System will pro- Mobile Servicing System will pro- vide greater mobility to Canadarm2, vide greater mobility to Canadarm2, vide greater mobility to Canadarm2, allow the transport of payloads allow the transport of payloads allow the transport of payloads across the ISS, and aid the crew in across the ISS, and aid the crew in across the ISS, and aid the crew in spacewalks spacewalks spacewalks Established: Fifth resident crew, Expedition 5, Established: Fifth resident crew, Expedition 5, Established: Fifth resident crew, Expedition 5, to the station: commander Valery to the station: commander Valery to the station: commander Valery Korzun and flight engineers Peggy Korzun and flight engineers Peggy Korzun and flight engineers Peggy Whitson and Sergei Treschev. Whitson and Sergei Treschev. Whitson and Sergei Treschev. Returned Expedition 4 crew to Returned Expedition 4 crew to Returned Expedition 4 crew to Earth. Expedition 4 crew members Earth. Expedition 4 crew members Earth. Expedition 4 crew members Carl Walz and Daniel Bursch set Carl Walz and Daniel Bursch set Carl Walz and Daniel Bursch set new record for longest U.S. space new record for longest U.S. space new record for longest U.S. space flight (196 days), breaking the pre- flight (196 days), breaking the pre- flight (196 days), breaking the pre- vious record of 188 days in space vious record of 188 days in space vious record of 188 days in space held by Shannon Lucid aboard the held by Shannon Lucid aboard the held by Shannon Lucid aboard the Russian space station Mir. Walz Russian space station Mir. Walz Russian space station Mir. Walz then set the U.S. record for the then set the U.S. record for the then set the U.S. record for the most cumulative time in space with most cumulative time in space with most cumulative time in space with 231 days. 231 days. 231 days.

9A/STS-112: Oct. 7, 2002 9A/STS-112: Oct. 7, 2002 9A/STS-112: Oct. 7, 2002 Launch Vehicle: Space shuttle Atlantis Launch Vehicle: Space shuttle Atlantis Launch Vehicle: Space shuttle Atlantis Elements: Starboard 1 (S1) truss Elements: Starboard 1 (S1) truss Elements: Starboard 1 (S1) truss Provided: The S1 truss contains a new Provided: The S1 truss contains a new Provided: The S1 truss contains a new external cooling system for the external cooling system for the external cooling system for the station that was activated on a later station that was activated on a later station that was activated on a later mission; also, a second S-band mission; also, a second S-band mission; also, a second S-band

B-64 B-64 B-64 communications system to provide communications system to provide communications system to provide enhanced and extended voice enhanced and extended voice enhanced and extended voice and data capability; the Crew and and data capability; the Crew and and data capability; the Crew and Equipment Translation Aid (CETA) Equipment Translation Aid (CETA) Equipment Translation Aid (CETA) cart that will serve as a mobile cart that will serve as a mobile cart that will serve as a mobile work platform for future spacewalk- work platform for future spacewalk- work platform for future spacewalk- ers; two new external television ers; two new external television ers; two new external television cameras; and the first thermal cameras; and the first thermal cameras; and the first thermal radiator rotary joint (TRRJ), which radiator rotary joint (TRRJ), which radiator rotary joint (TRRJ), which will provide the mechanical and will provide the mechanical and will provide the mechanical and electrical energy for rotating the electrical energy for rotating the electrical energy for rotating the station’s heat-rejecting radiators. station’s heat-rejecting radiators. station’s heat-rejecting radiators. The S1 truss will enable the station The S1 truss will enable the station The S1 truss will enable the station to begin the outboard expansion of to begin the outboard expansion of to begin the outboard expansion of its rail system in preparation for the its rail system in preparation for the its rail system in preparation for the addition of new power and science addition of new power and science addition of new power and science modules in the years to come. modules in the years to come. modules in the years to come.

11A/STS-113: Nov. 23, 2002 11A/STS-113: Nov. 23, 2002 11A/STS-113: Nov. 23, 2002 Launch Vehicle: Space shuttle Endeavour Launch Vehicle: Space shuttle Endeavour Launch Vehicle: Space shuttle Endeavour Elements: Port 1 (P1) truss and Crew and Elements: Port 1 (P1) truss and Crew and Elements: Port 1 (P1) truss and Crew and Equipment Translation Aid (CETA) Equipment Translation Aid (CETA) Equipment Translation Aid (CETA) cart cart cart Provided: The P1 truss, which is preintegrated Provided: The P1 truss, which is preintegrated Provided: The P1 truss, which is preintegrated with ultra-high frequency (UHF) with ultra-high frequency (UHF) with ultra-high frequency (UHF) communication equipment, thermal communication equipment, thermal communication equipment, thermal radiator rotary joint (TRRJ), three radiator rotary joint (TRRJ), three radiator rotary joint (TRRJ), three external active thermal control external active thermal control external active thermal control system (EATCS) radiators, direct system (EATCS) radiators, direct system (EATCS) radiators, direct current (DC)-to-DC converter unit current (DC)-to-DC converter unit current (DC)-to-DC converter unit (DDCU), remote power control- (DDCU), remote power control- (DDCU), remote power control- ler module (RPCM), nitrogen tank ler module (RPCM), nitrogen tank ler module (RPCM), nitrogen tank assembly (NTA), ammonia tank assembly (NTA), ammonia tank assembly (NTA), ammonia tank assembly (ATA), and pump module assembly (ATA), and pump module assembly (ATA), and pump module assembly (PMA) assembly (PMA) assembly (PMA) Established: Sixth resident crew, Expedition 6, Established: Sixth resident crew, Expedition 6, Established: Sixth resident crew, Expedition 6, to the station: commander Kenneth to the station: commander Kenneth to the station: commander Kenneth Bowersox, flight engineer Nikolai Bowersox, flight engineer Nikolai Bowersox, flight engineer Nikolai Budarin, and science officer Donald Budarin, and science officer Donald Budarin, and science officer Donald Pettit. Returned Expedition 5 crew Pettit. Returned Expedition 5 crew Pettit. Returned Expedition 5 crew to Earth to Earth to Earth

LF1/STS-114: July 26, 2005 LF1/STS-114: July 26, 2005 LF1/STS-114: July 26, 2005 Launch Vehicle: Space shuttle Discovery Launch Vehicle: Space shuttle Discovery Launch Vehicle: Space shuttle Discovery Elements: Raffaello MPLM carried equipment Elements: Raffaello MPLM carried equipment Elements: Raffaello MPLM carried equipment racks racks racks Provided: Test of orbiter boom sensor system Provided: Test of orbiter boom sensor system Provided: Test of orbiter boom sensor system (OBSS), test and evaluation of (OBSS), test and evaluation of (OBSS), test and evaluation of thermal protection system (TPS) thermal protection system (TPS) thermal protection system (TPS) repair techniques, replaced one repair techniques, replaced one repair techniques, replaced one ISS control gyroscope and restored ISS control gyroscope and restored ISS control gyroscope and restored power to a second gyroscope, power to a second gyroscope, power to a second gyroscope, installed work platform on ISS for installed work platform on ISS for installed work platform on ISS for future construction future construction future construction

B-65 B-65 B-65 ULF1.1/STS-121: July 4, 2006 ULF1.1/STS-121: July 4, 2006 ULF1.1/STS-121: July 4, 2006 Launch Vehicle: Space shuttle Discovery Launch Vehicle: Space shuttle Discovery Launch Vehicle: Space shuttle Discovery Elements: Leonardo MPLM carried equipment Elements: Leonardo MPLM carried equipment Elements: Leonardo MPLM carried equipment racks racks racks Provided: Additional test of orbiter boom sen- Provided: Additional test of orbiter boom sen- Provided: Additional test of orbiter boom sen- sor system (OBSS), additional test sor system (OBSS), additional test sor system (OBSS), additional test and evaluation of thermal protection and evaluation of thermal protection and evaluation of thermal protection system (TPS) repair techniques, system (TPS) repair techniques, system (TPS) repair techniques, replaced trailing umbilical system– replaced trailing umbilical system– replaced trailing umbilical system– reel assembly (TUS-RA) to restore reel assembly (TUS-RA) to restore reel assembly (TUS-RA) to restore station’s mobile robotic system to station’s mobile robotic system to station’s mobile robotic system to full operation full operation full operation Re-established: Three-person ISS crew for the first Re-established: Three-person ISS crew for the first Re-established: Three-person ISS crew for the first time since May 2003 time since May 2003 time since May 2003 12A/STS-115: Sept. 9, 2006 12A/STS-115: Sept. 9, 2006 12A/STS-115: Sept. 9, 2006 Launch Vehicle: Space shuttle Atlantis Launch Vehicle: Space shuttle Atlantis Launch Vehicle: Space shuttle Atlantis Elements: Port 3 and 4 (P3/P4) truss Elements: Port 3 and 4 (P3/P4) truss Elements: Port 3 and 4 (P3/P4) truss Provided: The P3 and P4 trusses are attached Provided: The P3 and P4 trusses are attached Provided: The P3 and P4 trusses are attached to the P1 truss and provide an to the P1 truss and provide an to the P1 truss and provide an attachment point for P5. The P3 and attachment point for P5. The P3 and attachment point for P5. The P3 and P4 trusses also provide a second P4 trusses also provide a second P4 trusses also provide a second set of solar array wings (SAWs) set of solar array wings (SAWs) set of solar array wings (SAWs) and the first alpha joint. The seg- and the first alpha joint. The seg- and the first alpha joint. The seg- ments support utility routing, power ments support utility routing, power ments support utility routing, power distribution, and a translation path distribution, and a translation path distribution, and a translation path for the mobile base system (MBS). for the mobile base system (MBS). for the mobile base system (MBS). Major P3 subsystems include the Major P3 subsystems include the Major P3 subsystems include the segment-to-segment attach system segment-to-segment attach system segment-to-segment attach system (SSAS), solar alpha rotary joint (SSAS), solar alpha rotary joint (SSAS), solar alpha rotary joint (SARJ), and unpressurized cargo (SARJ), and unpressurized cargo (SARJ), and unpressurized cargo carrier attach system (UCCAS). carrier attach system (UCCAS). carrier attach system (UCCAS). Major P4 subsystems include the Major P4 subsystems include the Major P4 subsystems include the photovoltaic radiator (PVR), alpha photovoltaic radiator (PVR), alpha photovoltaic radiator (PVR), alpha joint interface structure (AJIS), mod- joint interface structure (AJIS), mod- joint interface structure (AJIS), mod- ified Rocketdyne truss attachment ified Rocketdyne truss attachment ified Rocketdyne truss attachment system (MRTAS), and integrated system (MRTAS), and integrated system (MRTAS), and integrated equipment assembly (IEA). equipment assembly (IEA). equipment assembly (IEA). 12A.1/STS-116 Dec. 9, 2006 12A.1/STS-116 Dec. 9, 2006 12A.1/STS-116 Dec. 9, 2006 Launch Vehicle: Space shuttle Discovery Launch Vehicle: Space shuttle Discovery Launch Vehicle: Space shuttle Discovery Element: Port 5 (P5) truss Element: Port 5 (P5) truss Element: Port 5 (P5) truss Provided: The P5 is used primarily to connect Provided: The P5 is used primarily to connect Provided: The P5 is used primarily to connect power and cooling lines and serve power and cooling lines and serve power and cooling lines and serve as a spacer between the P4 and P6 as a spacer between the P4 and P6 as a spacer between the P4 and P6 photovoltaic modules. The girder- photovoltaic modules. The girder- photovoltaic modules. The girder- like structure provides several ex- like structure provides several ex- like structure provides several ex- travehicular aids, robotic interfaces, travehicular aids, robotic interfaces, travehicular aids, robotic interfaces, ammonia servicing hardware, and ammonia servicing hardware, and ammonia servicing hardware, and also can accommodate an external also can accommodate an external also can accommodate an external storage platform. P5 contains a storage platform. P5 contains a storage platform. P5 contains a remote sensor box, two tri-axial ac- remote sensor box, two tri-axial ac- remote sensor box, two tri-axial ac- celerators and two antenna assem- celerators and two antenna assem- celerators and two antenna assem- blies as part of the External Wireless blies as part of the External Wireless blies as part of the External Wireless Instrumentation System (EWIS). P5 Instrumentation System (EWIS). P5 Instrumentation System (EWIS). P5 also has white thermal blankets on also has white thermal blankets on also has white thermal blankets on the structure, which help shade the the structure, which help shade the the structure, which help shade the P4 solar array assembly ORUs. P4 solar array assembly ORUs. P4 solar array assembly ORUs.

B-66 B-66 B-66 13A/STS-117 June 8, 2007 13A/STS-117 June 8, 2007 13A/STS-117 June 8, 2007 Launch Vehicle: Space shuttle Atlantis Launch Vehicle: Space shuttle Atlantis Launch Vehicle: Space shuttle Atlantis Element: Starboard 3 and 4 (S3/S4) truss Element: Starboard 3 and 4 (S3/S4) truss Element: Starboard 3 and 4 (S3/S4) truss Provided: The principal functions of the S3 Provided: The principal functions of the S3 Provided: The principal functions of the S3 and S4 truss segments are to pro- and S4 truss segments are to pro- and S4 truss segments are to pro- vide electrical power and data inter- vide electrical power and data inter- vide electrical power and data inter- faces for future mission payloads faces for future mission payloads faces for future mission payloads and convert sunlight to electricity. and convert sunlight to electricity. and convert sunlight to electricity. The segments include another set The segments include another set The segments include another set of solar array wings (SAWs) and of solar array wings (SAWs) and of solar array wings (SAWs) and a second solar alpha rotary joint a second solar alpha rotary joint a second solar alpha rotary joint (SARJ), which keeps the arrays per- (SARJ), which keeps the arrays per- (SARJ), which keeps the arrays per- manently pointed toward the sun. manently pointed toward the sun. manently pointed toward the sun. Beside two SAWs and a SARJ, the Beside two SAWs and a SARJ, the Beside two SAWs and a SARJ, the S3/S4 structure has several distinct S3/S4 structure has several distinct S3/S4 structure has several distinct elements: the integrated equipment elements: the integrated equipment elements: the integrated equipment assembly (IEA), two beta gimbal assembly (IEA), two beta gimbal assembly (IEA), two beta gimbal assemblies (BGAs), and the photo- assemblies (BGAs), and the photo- assemblies (BGAs), and the photo- voltaic thermal control subsystem voltaic thermal control subsystem voltaic thermal control subsystem (PVTCS). (PVTCS). (PVTCS). 13A.1/STS-118 Aug. 8, 2007 13A.1/STS-118 Aug. 8, 2007 13A.1/STS-118 Aug. 8, 2007 Launch Vehicle: Space shuttle Endeavour Launch Vehicle: Space shuttle Endeavour Launch Vehicle: Space shuttle Endeavour Element: Starboard 5 (S5) truss Element: Starboard 5 (S5) truss Element: Starboard 5 (S5) truss Provided: The S5 will be used primarily to Provided: The S5 will be used primarily to Provided: The S5 will be used primarily to connect power, cooling lines, and connect power, cooling lines, and connect power, cooling lines, and serve as a spacer between the S4 serve as a spacer between the S4 serve as a spacer between the S4 photovoltaic module (PVM) and S6 photovoltaic module (PVM) and S6 photovoltaic module (PVM) and S6 PVM, which will be joined during a PVM, which will be joined during a PVM, which will be joined during a later assembly mission. S5 is very later assembly mission. S5 is very later assembly mission. S5 is very similar in construction to the long similar in construction to the long similar in construction to the long spacer located on S6. Without the spacer located on S6. Without the spacer located on S6. Without the S5 short spacer, the S4 and S6 S5 short spacer, the S4 and S6 S5 short spacer, the S4 and S6 solar arrays would not be able to solar arrays would not be able to solar arrays would not be able to connect because of the way the connect because of the way the connect because of the way the photovoltaic arrays (PVAs) are photovoltaic arrays (PVAs) are photovoltaic arrays (PVAs) are deployed on orbit. deployed on orbit. deployed on orbit. 10A/STS-120 Oct. 23, 2007 10A/STS-120 Oct. 23, 2007 10A/STS-120 Oct. 23, 2007 Launch Vehicle: Space shuttle Discovery Launch Vehicle: Space shuttle Discovery Launch Vehicle: Space shuttle Discovery Element: Node 2 “Harmony” Element: Node 2 “Harmony” Element: Node 2 “Harmony” Provided: Harmony added 2,666 cubic feet Provided: Harmony added 2,666 cubic feet Provided: Harmony added 2,666 cubic feet of living and working space to the of living and working space to the of living and working space to the complex, increasing the station’s liv- complex, increasing the station’s liv- complex, increasing the station’s liv- ing space by nearly 20%. It will serve ing space by nearly 20%. It will serve ing space by nearly 20%. It will serve as the permanent docking port for as the permanent docking port for as the permanent docking port for international laboratories from the international laboratories from the international laboratories from the ESA and JAXA. During STS-120, ESA and JAXA. During STS-120, ESA and JAXA. During STS-120, the crew installed Harmony in a the crew installed Harmony in a the crew installed Harmony in a temporary location and relocated temporary location and relocated temporary location and relocated the P6 truss segment and solar ar- the P6 truss segment and solar ar- the P6 truss segment and solar ar- rays to the end of the P5 truss, then rays to the end of the P5 truss, then rays to the end of the P5 truss, then redeployed and reactivated the P6 redeployed and reactivated the P6 redeployed and reactivated the P6 arrays. The Expedition 16 crew used arrays. The Expedition 16 crew used arrays. The Expedition 16 crew used Canadarm2 to move and install Canadarm2 to move and install Canadarm2 to move and install Harmony to its permanent location Harmony to its permanent location Harmony to its permanent location on the front of the Destiny laboratory on the front of the Destiny laboratory on the front of the Destiny laboratory after the shuttle departed. after the shuttle departed. after the shuttle departed.

B-67 B-67 B-67 1E/STS-122 Feb. 7, 2008 1E/STS-122 Feb. 7, 2008 1E/STS-122 Feb. 7, 2008 Launch Vehicle: Space shuttle Atlantis Launch Vehicle: Space shuttle Atlantis Launch Vehicle: Space shuttle Atlantis Element: Columbus Laboratory Element: Columbus Laboratory Element: Columbus Laboratory Provided: Columbus added 2,646 cubic feet Provided: Columbus added 2,646 cubic feet Provided: Columbus added 2,646 cubic feet of space to the ISS. It is the first of space to the ISS. It is the first of space to the ISS. It is the first European laboratory dedicated to European laboratory dedicated to European laboratory dedicated to long-term research in space and long-term research in space and long-term research in space and offers internal and external accom- offers internal and external accom- offers internal and external accom- modations for numerous experi- modations for numerous experi- modations for numerous experi- ments in life sciences, fluid physics, ments in life sciences, fluid physics, ments in life sciences, fluid physics, and a host of other disciplines. and a host of other disciplines. and a host of other disciplines. 1J/A/STS-123 March 11, 2008 1J/A/STS-123 March 11, 2008 1J/A/STS-123 March 11, 2008 Launch Vehicle: Space shuttle Endeavour Launch Vehicle: Space shuttle Endeavour Launch Vehicle: Space shuttle Endeavour Element: Kibo Japanese Experiment Element: Kibo Japanese Experiment Element: Kibo Japanese Experiment Logistics Module–Pressurized Logistics Module–Pressurized Logistics Module–Pressurized Section (ELM-PS) and Canadian Section (ELM-PS) and Canadian Section (ELM-PS) and Canadian Special Purpose Dexterous Special Purpose Dexterous Special Purpose Dexterous Manipulator (Dextre) Manipulator (Dextre) Manipulator (Dextre) Provided: The ELM-PS marks the beginning Provided: The ELM-PS marks the beginning Provided: The ELM-PS marks the beginning of JAXA’s presence on the ISS. of JAXA’s presence on the ISS. of JAXA’s presence on the ISS. ELM-PS is the smaller of two pres- ELM-PS is the smaller of two pres- ELM-PS is the smaller of two pres- surized Japanese modules. Com- surized Japanese modules. Com- surized Japanese modules. Com- bined with other elements delivered bined with other elements delivered bined with other elements delivered on shuttle missions STS-124 and on shuttle missions STS-124 and on shuttle missions STS-124 and STS-127, they will make up Kibo, STS-127, they will make up Kibo, STS-127, they will make up Kibo, the station’s largest science labora- the station’s largest science labora- the station’s largest science labora- tory. The addition of Dextre will al- tory. The addition of Dextre will al- tory. The addition of Dextre will al- low astronauts to replace hardware low astronauts to replace hardware low astronauts to replace hardware outside the station without doing a outside the station without doing a outside the station without doing a spacewalk. spacewalk. spacewalk. 1J/STS-124 May 31, 2008 1J/STS-124 May 31, 2008 1J/STS-124 May 31, 2008 Launch Vehicle: Space shuttle Discovery Launch Vehicle: Space shuttle Discovery Launch Vehicle: Space shuttle Discovery Element: Kibo Japanese Experiment Element: Kibo Japanese Experiment Element: Kibo Japanese Experiment Module–Pressurized Module Module–Pressurized Module Module–Pressurized Module (JEM-PM) and Japanese Experi- (JEM-PM) and Japanese Experi- (JEM-PM) and Japanese Experi- ment Module Remote Manipulator ment Module Remote Manipulator ment Module Remote Manipulator System (JEMRMS) System (JEMRMS) System (JEMRMS) Provided: The STS-124 mission was the Provided: The STS-124 mission was the Provided: The STS-124 mission was the second of three flights launching second of three flights launching second of three flights launching components to complete the Kibo components to complete the Kibo components to complete the Kibo laboratory. This mission delivered laboratory. This mission delivered laboratory. This mission delivered the JEM-PM, the central part of the JEM-PM, the central part of the JEM-PM, the central part of Kibo, the station’s largest science Kibo, the station’s largest science Kibo, the station’s largest science laboratory, and the main arm of the laboratory, and the main arm of the laboratory, and the main arm of the JEMRMS. JEMRMS. JEMRMS. ULF2/STS-126 Nov. 14, 2008 ULF2/STS-126 Nov. 14, 2008 ULF2/STS-126 Nov. 14, 2008 Launch Vehicle: Space shuttle Endeavour Launch Vehicle: Space shuttle Endeavour Launch Vehicle: Space shuttle Endeavour Element: Leonardo MPLM Element: Leonardo MPLM Element: Leonardo MPLM Provided: The STS-126 mission had two Provided: The STS-126 mission had two Provided: The STS-126 mission had two equally important goals: to deliver equally important goals: to deliver equally important goals: to deliver equipment—sleep stations, a new equipment—sleep stations, a new equipment—sleep stations, a new galley, an advanced resistive exer- galley, an advanced resistive exer- galley, an advanced resistive exer- cise device, and a water recovery cise device, and a water recovery cise device, and a water recovery

B-68 B-68 B-68 Provided (Cont'd): system—that will allow the station Provided (Cont'd): system—that will allow the station Provided (Cont'd): system—that will allow the station to double its crew size to six; plus to double its crew size to six; plus to double its crew size to six; plus the repair and maintenance of the the repair and maintenance of the the repair and maintenance of the Solar Alpha Rotary Joints, which Solar Alpha Rotary Joints, which Solar Alpha Rotary Joints, which rotate the ISS’s solar arrays to keep rotate the ISS’s solar arrays to keep rotate the ISS’s solar arrays to keep them facing the sun for maximum them facing the sun for maximum them facing the sun for maximum production of electricity. production of electricity. production of electricity. 15A/STS-119 March 15, 2009 15A/STS-119 March 15, 2009 15A/STS-119 March 15, 2009 Launch Vehicle: Space shuttle Discovery Launch Vehicle: Space shuttle Discovery Launch Vehicle: Space shuttle Discovery Element: Starboard 6 (S6) truss Element: Starboard 6 (S6) truss Element: Starboard 6 (S6) truss Provided: The STS-119 mission delivered Provided: The STS-119 mission delivered Provided: The STS-119 mission delivered the fourth set of solar arrays and the fourth set of solar arrays and the fourth set of solar arrays and batteries, completing the truss batteries, completing the truss batteries, completing the truss sys tem and doubling the amount system and doubling the amount system and doubling the amount of electricity available for science of electricity available for science of electricity available for science operations. operations. operations. 2J/A/STS-127 July 15, 2009 2J/A/STS-127 July 15, 2009 2J/A/STS-127 July 15, 2009 Launch Vehicle: Space shuttle Endeavour Launch Vehicle: Space shuttle Endeavour Launch Vehicle: Space shuttle Endeavour Element: Kibo Japanese Experiment Module Element: Kibo Japanese Experiment Module Element: Kibo Japanese Experiment Module Exposed Facility (JEM EF); Kibo Exposed Facility (JEM EF); Kibo Exposed Facility (JEM EF); Kibo Japanese Experiment Logistics Japanese Experiment Logistics Japanese Experiment Logistics Module–Exposed Section (ELM– Module–Exposed Section Module–Exposed Section ES) (ELM–ES) (ELM–ES) Provided: The JEM-EF is a part of Kibo that Provided: The JEM-EF is a part of Kibo that Provided: The JEM-EF is a part of Kibo that will allow astronauts to perform will allow astronauts to perform will allow astronauts to perform science experiments that are science experiments that are science experiments that are exposed to the vacuum of space. exposed to the vacuum of space. exposed to the vacuum of space. The ELM-ES is similar to the ELM- The ELM-ES is similar to the ELM- The ELM-ES is similar to the ELM- PS logistics module on Kibo but is PS logistics module on Kibo but is PS logistics module on Kibo but is not pressurized. Once its payloads not pressurized. Once its payloads not pressurized. Once its payloads are transferred to the JEM-EF, the are transferred to the JEM-EF, the are transferred to the JEM-EF, the ELM-ES is returned to the space ELM-ES is returned to the space ELM-ES is returned to the space shuttle’s payload bay. shuttle’s payload bay. shuttle’s payload bay. 17A/STS-128 Aug. 28, 2009 17A/STS-128 Aug. 28, 2009 17A/STS-128 Aug. 28, 2009 Launch Vehicle: Space shuttle Discovery Launch Vehicle: Space shuttle Discovery Launch Vehicle: Space shuttle Discovery Element: Leonardo MPLM; Lightweight Multi- Element: Leonardo MPLM; Lightweight Multi- Element: Leonardo MPLM; Lightweight Multi- purpose Carrier with Ammonia Tank purpose Carrier with Ammonia Tank purpose Carrier with Ammonia Tank Assembly Assembly Assembly Provided: Leonardo carried more than 16,000 Provided: Leonardo carried more than 16,000 Provided: Leonardo carried more than 16,000 pounds of supplies and equipment, pounds of supplies and equipment, pounds of supplies and equipment, including the Combined Operation- including the Combined Operation- including the Combined Operation- al Load Bearing External Resis- al Load Bearing External Resis- al Load Bearing External Resis- tance Treadmill (COLBERT); Fluids tance Treadmill (COLBERT); Fluids tance Treadmill (COLBERT); Fluids Integrated Rack, Materials Science Integrated Rack, Materials Science Integrated Rack, Materials Science Research Rack–1 and Minus Research Rack–1 and Minus Research Rack–1 and Minus Eighty-Degree Laboratory Freezer Eighty-Degree Laboratory Freezer Eighty-Degree Laboratory Freezer for ISS; and new crew quarters for for ISS; and new crew quarters for for ISS; and new crew quarters for Robert Thirsk. Robert Thirsk. Robert Thirsk.

B-69 B-69 B-69 ULF3/STS-129 Nov. 16, 2009 ULF3/STS-129 Nov. 16, 2009 ULF3/STS-129 Nov. 16, 2009 Launch Vehicle: Space shuttle Atlantis Launch Vehicle: Space shuttle Atlantis Launch Vehicle: Space shuttle Atlantis Element: ExPRESS Logistics Carrier 1 Element: ExPRESS Logistics Carrier 1 Element: ExPRESS Logistics Carrier 1 and 2 (ELC1 and ELC2) and 2 (ELC1 and ELC2) and 2 (ELC1 and ELC2) Provided: ELC1 and ELC2 carried numer- Provided: ELC1 and ELC2 carried numer- Provided: ELC1 and ELC2 carried numer- ous orbital replacement units too ous orbital replacement units too ous orbital replacement units too big to fly in any of the vehicles that big to fly in any of the vehicles that big to fly in any of the vehicles that will be left when the space shuttle will be left when the space shuttle will be left when the space shuttle retires, such as control moment retires, such as control moment retires, such as control moment gyroscopes, a battery charge gyroscopes, a battery charge gyroscopes, a battery charge discharge unit, a plasma contac- discharge unit, a plasma contac- discharge unit, a plasma contac- tor unit, nitrogen tanks, cooling tor unit, nitrogen tanks, cooling tor unit, nitrogen tanks, cooling system pump module assemblies, system pump module assemblies, system pump module assemblies, high-pressure gas tanks, ammonia high-pressure gas tanks, ammonia high-pressure gas tanks, ammonia tanks, a latching end effector for tanks, a latching end effector for tanks, a latching end effector for the station’s robotics, and a trailing the station’s robotics, and a trailing the station’s robotics, and a trailing umbilical system reel assembly. umbilical system reel assembly. umbilical system reel assembly.

B-70 B-70 B-70 Extravehicular Mobility Unit Extravehicular Mobility Unit Extravehicular Mobility Unit

The space shuttle and ISS extravehicular mobility unit The space shuttle and ISS extravehicular mobility unit The space shuttle and ISS extravehicular mobility unit (EMU), or spacesuit, has dramatically enabled humans (EMU), or spacesuit, has dramatically enabled humans (EMU), or spacesuit, has dramatically enabled humans to work effectively in space. Extravehicular activity (EVA), to work effectively in space. Extravehicular activity (EVA), to work effectively in space. Extravehicular activity (EVA), or spacewalk, highlights include the refueling and repair or spacewalk, highlights include the refueling and repair or spacewalk, highlights include the refueling and repair of satellites on orbit, retrieval of satellites for refurbishment of satellites on orbit, retrieval of satellites for refurbishment of satellites on orbit, retrieval of satellites for refurbishment on Earth, and the assembly of the ISS. The EMU has and on Earth, and the assembly of the ISS. The EMU has and on Earth, and the assembly of the ISS. The EMU has and will continue to play a vital role in allowing America’s space will continue to play a vital role in allowing America’s space will continue to play a vital role in allowing America’s space shuttle to fulfill a wide spectrum of space tasks such as shuttle to fulfill a wide spectrum of space tasks such as shuttle to fulfill a wide spectrum of space tasks such as inspection, maintenance, repair, construction, and, if inspection, maintenance, repair, construction, and, if inspection, maintenance, repair, construction, and, if necessary, rescue operations. necessary, rescue operations. necessary, rescue operations.

Hamilton Sundstrand Space Systems International pro- Hamilton Sundstrand Space Systems International pro- Hamilton Sundstrand Space Systems International pro- vides the EMU for NASA. The 394-lb EMU is modularized vides the EMU for NASA. The 394-lb EMU is modularized vides the EMU for NASA. The 394-lb EMU is modularized to fit astronauts and serves as a one-person spacecraft, to fit astronauts and serves as a one-person spacecraft, to fit astronauts and serves as a one-person spacecraft, providing protection and Earth-like mobility for EVA providing protection and Earth-like mobility for EVA providing protection and Earth-like mobility for EVA astronauts. It is constructed of a urethane-coated nylon astronauts. It is constructed of a urethane-coated nylon astronauts. It is constructed of a urethane-coated nylon pressure bladder; orthofabric and aluminized mylar pressure bladder; orthofabric and aluminized mylar pressure bladder; orthofabric and aluminized mylar thermal/meteoroid garment; fiberglass hard upper torso; thermal/meteoroid garment; fiberglass hard upper torso; thermal/meteoroid garment; fiberglass hard upper torso; ball-bearing joints (arm, wrist, leg); and polycarbonate ball-bearing joints (arm, wrist, leg); and polycarbonate ball-bearing joints (arm, wrist, leg); and polycarbonate helmet and visors. It provides a suit operating pressure helmet and visors. It provides a suit operating pressure helmet and visors. It provides a suit operating pressure of 4.3 psid in an operating environment ranging from 0 of 4.3 psid in an operating environment ranging from 0 of 4.3 psid in an operating environment ranging from 0 psia to 14.7 psia for as many as 7 hours. psia to 14.7 psia for as many as 7 hours. psia to 14.7 psia for as many as 7 hours.

Spacesuit assembly (SSA) provides: Spacesuit assembly (SSA) provides: Spacesuit assembly (SSA) provides: • Atmosphere containment • Atmosphere containment • Atmosphere containment • High-mobility and low-torque body joints • High-mobility and low-torque body joints • High-mobility and low-torque body joints • Thermal insulation • Thermal insulation • Thermal insulation • Cooling distribution • Cooling distribution • Cooling distribution • Waste collection • Waste collection • Waste collection

B-71 B-71 B-71 • Sunlight and solar radiation protection • Sunlight and solar radiation protection • Sunlight and solar radiation protection • Micrometeoroid and debris protection • Micrometeoroid and debris protection • Micrometeoroid and debris protection • Simple on-orbit resizing capability • Simple on-orbit resizing capability • Simple on-orbit resizing capability Life Support System (LSS) provides: Life Support System (LSS) provides: Life Support System (LSS) provides: • Oxygen supply • Oxygen supply • Oxygen supply • Suit pressurization and ventilation • Suit pressurization and ventilation • Suit pressurization and ventilation • Communications • Communications • Communications • Breathing gas purification • Breathing gas purification • Breathing gas purification • Temperature control • Temperature control • Temperature control • Independent emergency life support for up to • Independent emergency life support for up to • Independent emergency life support for up to 30 minutes 30 minutes 30 minutes • Orbital Replaceable Unit (ORU) capability • Orbital Replaceable Unit (ORU) capability • Orbital Replaceable Unit (ORU) capability For safety, the EMU is constantly monitored by a Caution For safety, the EMU is constantly monitored by a Caution For safety, the EMU is constantly monitored by a Caution and Warning System (CWS), which monitors 17 sensors, and Warning System (CWS), which monitors 17 sensors, and Warning System (CWS), which monitors 17 sensors, contaminant levels, and remaining expendables such as contaminant levels, and remaining expendables such as contaminant levels, and remaining expendables such as oxygen, water, and power. oxygen, water, and power. oxygen, water, and power. EVAs (as of January 2010) EVAs (as of January 2010) EVAs (as of January 2010)

Flight No. of EVAs Duration Flight No. of EVAs Duration Flight No. of EVAs Duration STS-88 3 21 hr, 22 min STS-88 3 21 hr, 22 min STS-88 3 21 hr, 22 min STS-96 1 7 hr, 55 min STS-96 1 7 hr, 55 min STS-96 1 7 hr, 55 min STS-101 1 6 hr, 44 min STS-101 1 6 hr, 44 min STS-101 1 6 hr, 44 min STS-106 1 6 hr, 14 min STS-106 1 6 hr, 14 min STS-106 1 6 hr, 14 min STS-92 4 27 hr, 19 min STS-92 4 27 hr, 19 min STS-92 4 27 hr, 19 min STS-97 3 19 hr, 20 min STS-97 3 19 hr, 20 min STS-97 3 19 hr, 20 min STS-98 3 19 hr, 49 min STS-98 3 19 hr, 49 min STS-98 3 19 hr, 49 min STS-102 2 15 hr, 17 min STS-102 2 15 hr, 17 min STS-102 2 15 hr, 17 min STS-100 2 14 hr, 50 min STS-100 2 14 hr, 50 min STS-100 2 14 hr, 50 min STS-104 2 12 hr, 28 min STS-104 2 12 hr, 28 min STS-104 2 12 hr, 28 min STS-105 2 11 hr, 45 min STS-105 2 11 hr, 45 min STS-105 2 11 hr, 45 min STS-108 1 4 hr, 12 min STS-108 1 4 hr, 12 min STS-108 1 4 hr, 12 min STS-114 3 20 hr, 05 min STS-114 3 20 hr, 05 min STS-114 3 20 hr, 05 min STS-121 3 21 hr, 29 min STS-121 3 21 hr, 29 min STS-121 3 21 hr, 29 min STS-115 3 20 hr, 19 min STS-115 3 20 hr, 19 min STS-115 3 20 hr, 19 min STS-116 4 25 hr, 45 min STS-116 4 25 hr, 45 min STS-116 4 25 hr, 45 min STS-117 4 27 hr, 58 min STS-117 4 27 hr, 58 min STS-117 4 27 hr, 58 min STS-118 4 23 hr, 15 min STS-118 4 23 hr, 15 min STS-118 4 23 hr, 15 min STS-120 4 27 hr, 14 min STS-120 4 27 hr, 14 min STS-120 4 27 hr, 14 min STS-122 3 22 hr, 08 min STS-122 3 22 hr, 08 min STS-122 3 22 hr, 08 min STS-123 5 33 hr, 28 min STS-123 5 33 hr, 28 min STS-123 5 33 hr, 28 min STS-124 3 20 hr, 32 min STS-124 3 20 hr, 32 min STS-124 3 20 hr, 32 min STS-126 4 26 hr, 41 min STS-126 4 26 hr, 41 min STS-126 4 26 hr, 41 min STS-119 3 19 hr, 04 min STS-119 3 19 hr, 04 min STS-119 3 19 hr, 04 min STS-127 5 30 hr, 30 min STS-127 5 30 hr, 30 min STS-127 5 30 hr, 30 min STS-128 3 20 hr, 15 min STS-128 3 20 hr, 15 min STS-128 3 20 hr, 15 min STS-129 3 18 hr, 27 min STS-129 3 18 hr, 27 min STS-129 3 18 hr, 27 min Total shuttle-based 28 187 hr, 20 min Total shuttle-based 28 187 hr, 20 min Total shuttle-based 28 187 hr, 20 min Total ISS-based 109 667 hr, 38 min Total ISS-based 109 667 hr, 38 min Total ISS-based 109 667 hr, 38 min Total to date 137 854 hr, 58 min Total to date 137 854 hr, 58 min Total to date 137 854 hr, 58 min

B-72 B-72 B-72 Future ISS Assembly Schedule (subject to change) Future ISS Assembly Schedule (subject to change) Future ISS Assembly Schedule (subject to change)

Assembly Launch Assembly Launch Assembly Launch Date Flight Vehicle Element(s) Date Flight Vehicle Element(s) Date Flight Vehicle Element(s) Targeted for 20A Endeavour • Node 3 "Tranquility" Targeted for 20A Endeavour • Node 3 "Tranquility" Targeted for 20A Endeavour • Node 3 "Tranquility" Feb. 2010 (OV-105) • Cupola Feb. 2010 (OV-105) • Cupola Feb. 2010 (OV-105) • Cupola STS-130 STS-130 STS-130

Targeted for 19A Discovery • Multi-Purpose Logistics Targeted for 19A Discovery • Multi-Purpose Logistics Targeted for 19A Discovery • Multi-Purpose Logistics March 2010 (OV-103) Module (MPLM) March 2010 (OV-103) Module (MPLM) March 2010 (OV-103) Module (MPLM) STS-131 • Lightweight Multi-Purpose STS-131 • Lightweight Multi-Purpose STS-131 • Lightweight Multi-Purpose Experiment Support Structure Experiment Support Structure Experiment Support Structure Carrier (LMC) Carrier (LMC) Carrier (LMC)

Targeted for ULF4 Atlantis • Integrated Cargo Carrier (ICC) Targeted for ULF4 Atlantis • Integrated Cargo Carrier (ICC) Targeted for ULF4 Atlantis • Integrated Cargo Carrier (ICC) May 2010 (OV-104) • Mini Research Module 1 May 2010 (OV-104) • Mini Research Module 1 May 2010 (OV-104) • Mini Research Module 1 STS-132 (MRM1) STS-132 (MRM1) STS-132 (MRM1)

Targeted for ULF6 Endeavour • ExPRESS Logistics Carrier 3 Targeted for ULF6 Endeavour • ExPRESS Logistics Carrier 3 Targeted for ULF6 Endeavour • ExPRESS Logistics Carrier 3 July 2010 (OV-105) (ELC3) July 2010 (OV-105) (ELC3) July 2010 (OV-105) (ELC3) STS-134 • Alpha Magnetic Spectrometer STS-134 • Alpha Magnetic Spectrometer STS-134 • Alpha Magnetic Spectrometer (AMS) (AMS) (AMS)

Targeted for ULF5 Discovery • ExPRESS Logistics Carrier 4 Targeted for ULF5 Discovery • ExPRESS Logistics Carrier 4 Targeted for ULF5 Discovery • ExPRESS Logistics Carrier 4 Sept. 2010 (OV-103) (ELC4) Sept. 2010 (OV-103) (ELC4) Sept. 2010 (OV-103) (ELC4) STS-133 • Multi-Purpose Logistics STS-133 • Multi-Purpose Logistics STS-133 • Multi-Purpose Logistics Module (MPLM) Module (MPLM) Module (MPLM)

Targeted for 3R Russian • Multipurpose Laboratory Targeted for 3R Russian • Multipurpose Laboratory Targeted for 3R Russian • Multipurpose Laboratory Dec. 2011 Proton Module with European Robotic Dec. 2011 Proton Module with European Robotic Dec. 2011 Proton Module with European Robotic Arm (ERA) Arm (ERA) Arm (ERA)

Note: Additional Progress, Soyuz, and European Automated Transfer Note: Additional Progress, Soyuz, and European Automated Transfer Note: Additional Progress, Soyuz, and European Automated Transfer Vehicle flights for crew transport, logistics, and resupply are not Vehicle flights for crew transport, logistics, and resupply are not Vehicle flights for crew transport, logistics, and resupply are not listed. listed. listed.

B-73 B-73 B-73 EXPEDITION CREWS EXPEDITION CREWS EXPEDITION CREWS

Human space flight history continues to be written each Human space flight history continues to be written each Human space flight history continues to be written each day aboard the International Space Station with the con- day aboard the International Space Station with the con- day aboard the International Space Station with the con- tinued human presence of each Expedition crew. tinued human presence of each Expedition crew. tinued human presence of each Expedition crew.

ISS began a new era in exploration by allowing humans to ISS began a new era in exploration by allowing humans to ISS began a new era in exploration by allowing humans to take up permanent residence in space. Many questions take up permanent residence in space. Many questions take up permanent residence in space. Many questions about how to sustain life in outer space were previously about how to sustain life in outer space were previously about how to sustain life in outer space were previously answered during NASA’s experience with the Shuttle/Mir answered during NASA’s experience with the Shuttle/Mir answered during NASA’s experience with the Shuttle/Mir program. This knowledge, combined with the discoveries program. This knowledge, combined with the discoveries program. This knowledge, combined with the discoveries of the astronauts and cosmonauts living on board ISS, of the astronauts and cosmonauts living on board ISS, of the astronauts and cosmonauts living on board ISS, will greatly increase our understanding of what it is like will greatly increase our understanding of what it is like will greatly increase our understanding of what it is like living in space. living in space. living in space.

The crews rotate during crew exchange flights. During the The crews rotate during crew exchange flights. During the The crews rotate during crew exchange flights. During the hand-over period, the current space station crew members hand-over period, the current space station crew members hand-over period, the current space station crew members communicate by conference call to the new crew members communicate by conference call to the new crew members communicate by conference call to the new crew members any rare situations they have dealt with, any new tech- any rare situations they have dealt with, any new tech- any rare situations they have dealt with, any new tech- niques they have learned, or any information that might be niques they have learned, or any information that might be niques they have learned, or any information that might be helpful to the new residents. Once the new crew members helpful to the new residents. Once the new crew members helpful to the new residents. Once the new crew members actually arrive, the outgoing crew will brief them on safety, actually arrive, the outgoing crew will brief them on safety, actually arrive, the outgoing crew will brief them on safety, vehicle changes, and payload operations. vehicle changes, and payload operations. vehicle changes, and payload operations.

The current habitable pressurized volume on ISS—15,000 The current habitable pressurized volume on ISS—15,000 The current habitable pressurized volume on ISS—15,000 cubic feet (425 cubic meters)—is equal to the habitable cubic feet (425 cubic meters)—is equal to the habitable cubic feet (425 cubic meters)—is equal to the habitable space in a 1,800-square-foot (167-square-meter) three- space in a 1,800-square-foot (167-square-meter) three- space in a 1,800-square-foot (167-square-meter) three- bedroom house with 8-foot (2.4-meter) ceilings. The habit- bedroom house with 8-foot (2.4-meter) ceilings. The habit- bedroom house with 8-foot (2.4-meter) ceilings. The habit- able pressurized volume on the completed station will be able pressurized volume on the completed station will be able pressurized volume on the completed station will be 34,700 cubic feet (983 cubic meters), roughly equivalent 34,700 cubic feet (983 cubic meters), roughly equivalent 34,700 cubic feet (983 cubic meters), roughly equivalent to the interior of a Boeing 747. to the interior of a Boeing 747. to the interior of a Boeing 747.

Expedition 1 Expedition 1 Expedition 1 Mission: ISS Flight 2R Mission: ISS Flight 2R Mission: ISS Flight 2R Vehicle: Soyuz TM-31 Vehicle: Soyuz TM-31 Vehicle: Soyuz TM-31 Launched: Oct. 31, 2000, from Baikonur Launched: Oct. 31, 2000, from Baikonur Launched: Oct. 31, 2000, from Baikonur Cosmodrome in Kazakhstan Cosmodrome in Kazakhstan Cosmodrome in Kazakhstan Crew: ISS commander Bill Shepherd Crew: ISS commander Bill Shepherd Crew: ISS commander Bill Shepherd Soyuz commander Yuri Gidzenko Soyuz commander Yuri Gidzenko Soyuz commander Yuri Gidzenko Flight engineer Sergei Krikalev Flight engineer Sergei Krikalev Flight engineer Sergei Krikalev Returned: March 21, 2001, aboard STS-102 Returned: March 21, 2001, aboard STS-102 Returned: March 21, 2001, aboard STS-102 (Discovery) (Discovery) (Discovery) Duration: 141 days Duration: 141 days Duration: 141 days Expedition 2 Expedition 2 Expedition 2 Mission: STS-102/ISS Flight 5A.1 Mission: STS-102/ISS Flight 5A.1 Mission: STS-102/ISS Flight 5A.1 Vehicle: Space shuttle Discovery Vehicle: Space shuttle Discovery Vehicle: Space shuttle Discovery Launched: March 8, 2001, from Kennedy Launched: March 8, 2001, from Kennedy Launched: March 8, 2001, from Kennedy Space Center, Pad 39B Space Center, Pad 39B Space Center, Pad 39B Crew: ISS commander Yury Usachev Crew: ISS commander Yury Usachev Crew: ISS commander Yury Usachev Flight engineer James Voss Flight engineer James Voss Flight engineer James Voss Flight engineer Susan Helms Flight engineer Susan Helms Flight engineer Susan Helms Returned: Aug. 22, 2001, aboard STS-105 Returned: Aug. 22, 2001, aboard STS-105 Returned: Aug. 22, 2001, aboard STS-105 (Discovery) (Discovery) (Discovery) Duration: 167 days Duration: 167 days Duration: 167 days

B-74 B-74 B-74 Expedition 3 Expedition 3 Expedition 3 Mission: STS-105/ISS Flight 7A.1 Mission: STS-105/ISS Flight 7A.1 Mission: STS-105/ISS Flight 7A.1 Vehicle: Space shuttle Discovery Vehicle: Space shuttle Discovery Vehicle: Space shuttle Discovery Launched: Aug. 10, 2001, from Kennedy Launched: Aug. 10, 2001, from Kennedy Launched: Aug. 10, 2001, from Kennedy Space Center, Pad 39A Space Center, Pad 39A Space Center, Pad 39A Crew: ISS commander Frank Culbertson Jr., Crew: ISS commander Frank Culbertson Jr., Crew: ISS commander Frank Culbertson Jr., Soyuz commander Vladimir Dezhurov Soyuz commander Vladimir Dezhurov Soyuz commander Vladimir Dezhurov Flight engineer Mikhail Tyurin Flight engineer Mikhail Tyurin Flight engineer Mikhail Tyurin Returned: Dec. 17, 2001, aboard STS-108 Returned: Dec. 17, 2001, aboard STS-108 Returned: Dec. 17, 2001, aboard STS-108 (Endeavour) (Endeavour) (Endeavour) Duration: 129 days Duration: 129 days Duration: 129 days Expedition 4 Expedition 4 Expedition 4 Mission: STS-108/ISS Flight UF-1 Mission: STS-108/ISS Flight UF-1 Mission: STS-108/ISS Flight UF-1 Vehicle: Space shuttle Endeavour Vehicle: Space shuttle Endeavour Vehicle: Space shuttle Endeavour Launched: Dec. 5, 2001, from Kennedy Space Launched: Dec. 5, 2001, from Kennedy Space Launched: Dec. 5, 2001, from Kennedy Space Center, Pad 39B Center, Pad 39B Center, Pad 39B Crew: ISS commander Yury I. Onufrienko Crew: ISS commander Yury I. Onufrienko Crew: ISS commander Yury I. Onufrienko Flight engineer Daniel W. Bursch Flight engineer Daniel W. Bursch Flight engineer Daniel W. Bursch Flight engineer Carl E. Walz Flight engineer Carl E. Walz Flight engineer Carl E. Walz Returned: June 19, 2002, aboard STS-111 Returned: June 19, 2002, aboard STS-111 Returned: June 19, 2002, aboard STS-111 (Endeavour) (Endeavour) (Endeavour) Duration: 196 days Duration: 196 days Duration: 196 days Expedition 5 Expedition 5 Expedition 5 Mission: STS-111/ISS Flight UF-2 Mission: STS-111/ISS Flight UF-2 Mission: STS-111/ISS Flight UF-2 Vehicle: Space shuttle Endeavour Vehicle: Space shuttle Endeavour Vehicle: Space shuttle Endeavour Launched: June 5, 2002, from Kennedy Space Launched: June 5, 2002, from Kennedy Space Launched: June 5, 2002, from Kennedy Space Center, Pad 39A Center, Pad 39A Center, Pad 39A Crew: ISS commander Valery G. Korzun Crew: ISS commander Valery G. Korzun Crew: ISS commander Valery G. Korzun ISS science officer ISS science officer ISS science officer Peggy A. Whitson Peggy A. Whitson Peggy A. Whitson Flight engineer Sergei Y. Treschev Flight engineer Sergei Y. Treschev Flight engineer Sergei Y. Treschev Returned: Dec. 7, 2002, aboard STS-113 Returned: Dec. 7, 2002, aboard STS-113 Returned: Dec. 7, 2002, aboard STS-113 (Endeavour) (Endeavour) (Endeavour) Duration: 185 days Duration: 185 days Duration: 185 days Expedition 6 Expedition 6 Expedition 6 Mission: STS-113/ISS Flight 11A Mission: STS-113/ISS Flight 11A Mission: STS-113/ISS Flight 11A Vehicle: Space shuttle Endeavour Vehicle: Space shuttle Endeavour Vehicle: Space shuttle Endeavour Launched: Nov. 23, 2002, from Kennedy Launched: Nov. 23, 2002, from Kennedy Launched: Nov. 23, 2002, from Kennedy Space Center, Pad 39A Space Center, Pad 39A Space Center, Pad 39A Crew: ISS commander Crew: ISS commander Crew: ISS commander Kenneth D. Bowersox Kenneth D. Bowersox Kenneth D. Bowersox Flight engineer Nikolai M. Budarin Flight engineer Nikolai M. Budarin Flight engineer Nikolai M. Budarin ISS science officer Donald R. Pettit ISS science officer Donald R. Pettit ISS science officer Donald R. Pettit Returned: May 3, 2003, aboard Soyuz TMA-1 Returned: May 3, 2003, aboard Soyuz TMA-1 Returned: May 3, 2003, aboard Soyuz TMA-1 Duration: 161 days Duration: 161 days Duration: 161 days Expedition 7 Expedition 7 Expedition 7 Vehicle: Soyuz TMA-2 Vehicle: Soyuz TMA-2 Vehicle: Soyuz TMA-2 Launched: April 25, 2003, from Baikonur Launched: April 25, 2003, from Baikonur Launched: April 25, 2003, from Baikonur Cosmodrome in Kazakhstan Cosmodrome in Kazakhstan Cosmodrome in Kazakhstan Crew: ISS commander Yuri I. Malenchenko Crew: ISS commander Yuri I. Malenchenko Crew: ISS commander Yuri I. Malenchenko Flight engineer/science officer Flight engineer/science officer Flight engineer/science officer Edward T. Lu Edward T. Lu Edward T. Lu Returned: Oct. 27, 2003, aboard Soyuz TMA-2 Returned: Oct. 27, 2003, aboard Soyuz TMA-2 Returned: Oct. 27, 2003, aboard Soyuz TMA-2 Duration: 185 days Duration: 185 days Duration: 185 days B-75 B-75 B-75 Expedition 8 Expedition 8 Expedition 8 Vehicle: Soyuz TMA-3 Vehicle: Soyuz TMA-3 Vehicle: Soyuz TMA-3 Launched: Oct. 18, 2003, from Baikonur Launched: Oct. 18, 2003, from Baikonur Launched: Oct. 18, 2003, from Baikonur Cosmodrome in Kazakhstan Cosmodrome in Kazakhstan Cosmodrome in Kazakhstan Crew: ISS commander/science officer Crew: ISS commander/science officer Crew: ISS commander/science officer C. Michael Foale C. Michael Foale C. Michael Foale Flight engineer Alexander Y. Kaleri Flight engineer Alexander Y. Kaleri Flight engineer Alexander Y. Kaleri Flight engineer Pedro Duque Flight engineer Pedro Duque Flight engineer Pedro Duque (launched with Expedition 8, (launched with Expedition 8, (launched with Expedition 8, returned with Expedition 7) returned with Expedition 7) returned with Expedition 7) Returned: April 29, 2004, aboard Soyuz TMA-3 Returned: April 29, 2004, aboard Soyuz TMA-3 Returned: April 29, 2004, aboard Soyuz TMA-3 Duration: 195 days Duration: 195 days Duration: 195 days Expedition 9 Expedition 9 Expedition 9 Vehicle: Soyuz TMA-4 Vehicle: Soyuz TMA-4 Vehicle: Soyuz TMA-4 Launched: April 18, 2004, from Baikonur Launched: April 18, 2004, from Baikonur Launched: April 18, 2004, from Baikonur Cosmodrome in Kazakhstan Cosmodrome in Kazakhstan Cosmodrome in Kazakhstan Crew: ISS commander Crew: ISS commander Crew: ISS commander Gennady I. Padalka Gennady I. Padalka Gennady I. Padalka Flight engineer/science officer Flight engineer/science officer Flight engineer/science officer E. Michael Fincke E. Michael Fincke E. Michael Fincke Flight engineer André Kuipers Flight engineer André Kuipers Flight engineer André Kuipers (launched with Expedition 9, (launched with Expedition 9, (launched with Expedition 9, returned with Expedition 8) returned with Expedition 8) returned with Expedition 8) Returned: Oct. 23, 2004, aboard Soyuz TMA-4 Returned: Oct. 23, 2004, aboard Soyuz TMA-4 Returned: Oct. 23, 2004, aboard Soyuz TMA-4 Duration: 188 days Duration: 188 days Duration: 188 days Expedition 10 Expedition 10 Expedition 10 Vehicle: Soyuz TMA-5 Vehicle: Soyuz TMA-5 Vehicle: Soyuz TMA-5 Launched: Oct. 13, 2004, from Baikonur Launched: Oct. 13, 2004, from Baikonur Launched: Oct. 13, 2004, from Baikonur Cosmodrome in Kazakhstan Cosmodrome in Kazakhstan Cosmodrome in Kazakhstan Crew: ISS commander/science officer Crew: ISS commander/science officer Crew: ISS commander/science officer Leroy Chiao Leroy Chiao Leroy Chiao Flight engineer Salizhan S. Sharipov Flight engineer Salizhan S. Sharipov Flight engineer Salizhan S. Sharipov Flight engineer Yuri G. Shargin Flight engineer Yuri G. Shargin Flight engineer Yuri G. Shargin (launched with Expedition 10, (launched with Expedition 10, (launched with Expedition 10, returned with Expedition 9) returned with Expedition 9) returned with Expedition 9) Returned: April 24, 2005, aboard Soyuz TMA-5 Returned: April 24, 2005, aboard Soyuz TMA-5 Returned: April 24, 2005, aboard Soyuz TMA-5 Duration: 193 days Duration: 193 days Duration: 193 days Expedition 11 Expedition 11 Expedition 11 Vehicle: Soyuz TMA-6 Vehicle: Soyuz TMA-6 Vehicle: Soyuz TMA-6 Launched: April 14, 2005, from Baikonur Launched: April 14, 2005, from Baikonur Launched: April 14, 2005, from Baikonur Cosmodrome in Kazakhstan Cosmodrome in Kazakhstan Cosmodrome in Kazakhstan Crew: ISS commander Sergei K. Krikalev Crew: ISS commander Sergei K. Krikalev Crew: ISS commander Sergei K. Krikalev Flight engineer/science officer Flight engineer/science officer Flight engineer/science officer John L. Phillips John L. Phillips John L. Phillips Flight engineer Roberto Vittori Flight engineer Roberto Vittori Flight engineer Roberto Vittori (launched with Expedition 11, (launched with Expedition 11, (launched with Expedition 11, returned with Expedition 10) returned with Expedition 10) returned with Expedition 10) Returned: Oct. 10, 2005, aboard Soyuz TMA-6 Returned: Oct. 10, 2005, aboard Soyuz TMA-6 Returned: Oct. 10, 2005, aboard Soyuz TMA-6 Duration: 179 days Duration: 179 days Duration: 179 days

B-76 B-76 B-76 Expedition 12 Expedition 12 Expedition 12 Vehicle: TMA-7 Vehicle: TMA-7 Vehicle: TMA-7 Launched: Sept. 30, 2005, from Baikonur Launched: Sept. 30, 2005, from Baikonur Launched: Sept. 30, 2005, from Baikonur Cosmodrome in Kazakhstan Cosmodrome in Kazakhstan Cosmodrome in Kazakhstan Crew: ISS commander/science officer Crew: ISS commander/science officer Crew: ISS commander/science officer William McArthur William McArthur William McArthur Flight engineer Valery Tokarev Flight engineer Valery Tokarev Flight engineer Valery Tokarev Returned: April 8, 2005, aboard Soyuz TMA-7 Returned: April 8, 2005, aboard Soyuz TMA-7 Returned: April 8, 2005, aboard Soyuz TMA-7 Duration: 190 days Duration: 190 days Duration: 190 days Expedition 13 Expedition 13 Expedition 13 Vehicle: Soyuz TMA-8 Vehicle: Soyuz TMA-8 Vehicle: Soyuz TMA-8 Launched: March 29, 2006, from Baikonur Launched: March 29, 2006, from Baikonur Launched: March 29, 2006, from Baikonur Cosmodrome in Kazakhstan Cosmodrome in Kazakhstan Cosmodrome in Kazakhstan Crew: ISS commander/Soyuz commander Crew: ISS commander/Soyuz commander Crew: ISS commander/Soyuz commander Pavel Vinogradov Pavel Vinogradov Pavel Vinogradov Flight engineer/science officer Flight engineer/science officer Flight engineer/science officer Jeffrey Williams Jeffrey Williams Jeffrey Williams Flight engineer Marcus Pontes Flight engineer Marcus Pontes Flight engineer Marcus Pontes (launched with Expedition 13, (launched with Expedition 13, (launched with Expedition 13, returned with Expedition 12) returned with Expedition 12) returned with Expedition 12) Flight engineer Thomas Reiter Flight engineer Thomas Reiter Flight engineer Thomas Reiter (launched aboard STS-121, (launched aboard STS-121, (launched aboard STS-121, returned aboard STS-116) returned aboard STS-116) returned aboard STS-116) Returned: Sept. 28, 2006, aboard Soyuz TMA-8 Returned: Sept. 28, 2006, aboard Soyuz TMA-8 Returned: Sept. 28, 2006, aboard Soyuz TMA-8 Duration: 183 days Duration: 183 days Duration: 183 days Expedition 14 Expedition 14 Expedition 14 Vehicle: Soyuz TMA-9 Vehicle: Soyuz TMA-9 Vehicle: Soyuz TMA-9 Launched: Sept. 18, 2006, from Baikonur Launched: Sept. 18, 2006, from Baikonur Launched: Sept. 18, 2006, from Baikonur Cosmodrome in Kazakhstan Cosmodrome in Kazakhstan Cosmodrome in Kazakhstan Crew: ISS commander Crew: ISS commander Crew: ISS commander Michael E. Lopez-Alegria* Michael E. Lopez-Alegria* Michael E. Lopez-Alegria* *Lopez-Alegria set new U.S. *Lopez-Alegria set new U.S. *Lopez-Alegria set new U.S. record for continuous time record for continuous time record for continuous time in space of 215 days. in space of 215 days. in space of 215 days. Flight engineer Mikhail Tyurin Flight engineer Mikhail Tyurin Flight engineer Mikhail Tyurin Flight engineer Thomas Reiter Flight engineer Thomas Reiter Flight engineer Thomas Reiter (launched aboard STS-121, (launched aboard STS-121, (launched aboard STS-121, returned aboard STS-116) returned aboard STS-116) returned aboard STS-116) Flight engineer Sunita L. Williams Flight engineer Sunita L. Williams Flight engineer Sunita L. Williams (launched aboard STS-116, (launched aboard STS-116, (launched aboard STS-116, returned aboard STS-117) returned aboard STS-117) returned aboard STS-117) Returned: April 21, 2007, aboard Soyuz TMA-9 Returned: April 21, 2007, aboard Soyuz TMA-9 Returned: April 21, 2007, aboard Soyuz TMA-9 Duration: 215 days Duration: 215 days Duration: 215 days Expedition 15 Expedition 15 Expedition 15 Vehicle: Soyuz TMA-10 Vehicle: Soyuz TMA-10 Vehicle: Soyuz TMA-10 Launched: April 7, 2007, from Baikonur Launched: April 7, 2007, from Baikonur Launched: April 7, 2007, from Baikonur Cosmodrome in Kazakhstan Cosmodrome in Kazakhstan Cosmodrome in Kazakhstan Crew: ISS commander Fyodor N. Yurchikhin Crew: ISS commander Fyodor N. Yurchikhin Crew: ISS commander Fyodor N. Yurchikhin Flight engineer Oleg V. Kotov Flight engineer Oleg V. Kotov Flight engineer Oleg V. Kotov Flight engineer Sunita L. Williams Flight engineer Sunita L. Williams Flight engineer Sunita L. Williams (launched aboard STS-116, (launched aboard STS-116, (launched aboard STS-116, returned aboard STS-117) returned aboard STS-117) returned aboard STS-117) Flight engineer Clayton C. Anderson Flight engineer Clayton C. Anderson Flight engineer Clayton C. Anderson (launched aboard STS-117, (launched aboard STS-117, (launched aboard STS-117, returned aboard STS-120) returned aboard STS-120) returned aboard STS-120)

B-77 B-77 B-77 Crew (Cont'd): Flight engineer Daniel M. Tani Crew (Cont'd): Flight engineer Daniel M. Tani Crew (Cont'd): Flight engineer Daniel M. Tani (launched aboard STS-120, (launched aboard STS-120, (launched aboard STS-120, returned aboard STS-122) returned aboard STS-122) returned aboard STS-122) Returned: October 21, 2007, aboard Soyuz Returned: October 21, 2007, aboard Soyuz Returned: October 21, 2007, aboard Soyuz TMA-10 TMA-10 TMA-10 Duration: 196 days Duration: 196 days Duration: 196 days Expedition 16 Expedition 16 Expedition 16 Vehicle: Soyuz TMA-11 Vehicle: Soyuz TMA-11 Vehicle: Soyuz TMA-11 Launched: October 10, 2007, from Baikonur Launched: October 10, 2007, from Baikonur Launched: October 10, 2007, from Baikonur Cosmodrome in Kazakhstan Cosmodrome in Kazakhstan Cosmodrome in Kazakhstan Crew: ISS commander Peggy A. Whitson Crew: ISS commander Peggy A. Whitson Crew: ISS commander Peggy A. Whitson Soyuz commander/flight engineer Soyuz commander/flight engineer Soyuz commander/flight engineer Yuri I. Malenchenko Yuri I. Malenchenko Yuri I. Malenchenko Flight engineer Flight engineer Flight engineer Clayton C. Anderson Clayton C. Anderson Clayton C. Anderson (launched aboard STS-117, (launched aboard STS-117, (launched aboard STS-117, returned aboard STS-120) returned aboard STS-120) returned aboard STS-120) Flight engineer Daniel M. Tani Flight engineer Daniel M. Tani Flight engineer Daniel M. Tani (launched aboard STS-120, (launched aboard STS-120, (launched aboard STS-120, returned aboard STS-122) returned aboard STS-122) returned aboard STS-122) Flight engineer Leopold Eyharts Flight engineer Leopold Eyharts Flight engineer Leopold Eyharts (launched aboard STS-122, (launched aboard STS-122, (launched aboard STS-122, returned aboard STS-123) returned aboard STS-123) returned aboard STS-123) Flight engineer Garrett E. Reisman Flight engineer Garrett E. Reisman Flight engineer Garrett E. Reisman (launched aboard STS-123, (launched aboard STS-123, (launched aboard STS-123, returned aboard STS-124) returned aboard STS-124) returned aboard STS-124) Returned: April 19, 2008, aboard Returned: April 19, 2008, aboard Returned: April 19, 2008, aboard Soyuz TMA-11 Soyuz TMA-11 Soyuz TMA-11 Duration: 192 days Duration: 192 days Duration: 192 days Expedition 17 Expedition 17 Expedition 17 Vehicle: Soyuz TMA-12 Vehicle: Soyuz TMA-12 Vehicle: Soyuz TMA-12 Launched: April 8, 2008, from Baikonur Launched: April 8, 2008, from Baikonur Launched: April 8, 2008, from Baikonur Cosmodrome in Kazakhstan Cosmodrome in Kazakhstan Cosmodrome in Kazakhstan Crew: ISS commander/Soyuz commander Crew: ISS commander/Soyuz commander Crew: ISS commander/Soyuz commander Sergei A. Volkov Sergei A. Volkov Sergei A. Volkov Flight engineer Oleg D. Kononenko Flight engineer Oleg D. Kononenko Flight engineer Oleg D. Kononenko Flight engineer Garrett E. Reisman Flight engineer Garrett E. Reisman Flight engineer Garrett E. Reisman (launched aboard STS-123, (launched aboard STS-123, (launched aboard STS-123, returned aboard STS-124) returned aboard STS-124) returned aboard STS-124) Flight engineer Gregory E. Flight engineer Gregory E. Flight engineer Gregory E. Chamitoff (launched aboard Chamitoff (launched aboard Chamitoff (launched aboard STS-124, returned aboard STS-126) STS-124, returned aboard STS-126) STS-124, returned aboard STS-126) Flight engineer Sandra H. Magnus Flight engineer Sandra H. Magnus Flight engineer Sandra H. Magnus (launched aboard STS-126, return (launched aboard STS-126, return (launched aboard STS-126, return aboard STS-119) aboard STS-119) aboard STS-119) Of Note: First mission to use all three partner Of Note: First mission to use all three partner Of Note: First mission to use all three partner laboratories—the U.S. Destiny, laboratories—the U.S. Destiny, laboratories—the U.S. Destiny, European Columbus, and the European Columbus, and the European Columbus, and the Japanese Kibo. First mission to be Japanese Kibo. First mission to be Japanese Kibo. First mission to be supported by four different resupply supported by four different resupply supported by four different resupply vehicles—the space shuttle, Soyuz, vehicles—the space shuttle, Soyuz, vehicles—the space shuttle, Soyuz, Progress, and European Automat- Progress, and European Automat- Progress, and European Automat- ed Transfer Vehicle. First mission ed Transfer Vehicle. First mission ed Transfer Vehicle. First mission to use three robotic systems— to use three robotic systems— to use three robotic systems— Canadarm2, Dextre, and Kibo’s Canadarm2, Dextre, and Kibo’s Canadarm2, Dextre, and Kibo’s JEMRMS. JEMRMS. JEMRMS.

B-78 B-78 B-78 Of Note (Cont'd): First mission to be commanded by Of Note (Cont'd): First mission to be commanded by Of Note (Cont'd): First mission to be commanded by a second-generation cosmonaut; a second-generation cosmonaut; a second-generation cosmonaut; commander Sergei Volkov is the commander Sergei Volkov is the commander Sergei Volkov is the son of former cosmonaut Alexander son of former cosmonaut Alexander son of former cosmonaut Alexander Volkov, who served on Salyut 7 and Volkov, who served on Salyut 7 and Volkov, who served on Salyut 7 and the Mir space station. the Mir space station. the Mir space station. Returned: October 23, 2008, aboard Soyuz Returned: October 23, 2008, aboard Soyuz Returned: October 23, 2008, aboard Soyuz TMA-12 TMA-12 TMA-12 Duration: 199 days Duration: 199 days Duration: 199 days Expedition 18 Expedition 18 Expedition 18 Vehicle: Soyuz TMA-13 Vehicle: Soyuz TMA-13 Vehicle: Soyuz TMA-13 Launched: October 12, 2008, from Baikonur Launched: October 12, 2008, from Baikonur Launched: October 12, 2008, from Baikonur Cosmodrome in Kazakhstan Cosmodrome in Kazakhstan Cosmodrome in Kazakhstan Crew: ISS commander E. Michael Fincke Crew: ISS commander E. Michael Fincke Crew: ISS commander E. Michael Fincke Flight engineer/Soyuz commander Flight engineer/Soyuz commander Flight engineer/Soyuz commander Yuri V. Lonchakov Yuri V. Lonchakov Yuri V. Lonchakov Flight engineer Gregory E. Flight engineer Gregory E. Flight engineer Gregory E. Chamitoff Chamitoff Chamitoff (launched aboard STS-124, (launched aboard STS-124, (launched aboard STS-124, returned aboard STS-126) returned aboard STS-126) returned aboard STS-126) Flight engineer Sandra H. Magnus Flight engineer Sandra H. Magnus Flight engineer Sandra H. Magnus (launched aboard STS-126, (launched aboard STS-126, (launched aboard STS-126, returned aboard STS-119) returned aboard STS-119) returned aboard STS-119) Flight engineer Koichi Wakata Flight engineer Koichi Wakata Flight engineer Koichi Wakata (launched aboard STS-119, (launched aboard STS-119, (launched aboard STS-119, return aboard STS-127) return aboard STS-127) return aboard STS-127) Returned: April 8, 2009 Returned: April 8, 2009 Returned: April 8, 2009 Duration: 178 days Duration: 178 days Duration: 178 days Expedition 19 Expedition 19 Expedition 19 Vehicle: Soyuz TMA-14 Vehicle: Soyuz TMA-14 Vehicle: Soyuz TMA-14 Launched: March 26, 2009, from Baikonur Launched: March 26, 2009, from Baikonur Launched: March 26, 2009, from Baikonur Cosmodrome in Kazakhstan Cosmodrome in Kazakhstan Cosmodrome in Kazakhstan Crew: ISS commander/Soyuz commander Crew: ISS commander/Soyuz commander Crew: ISS commander/Soyuz commander Gennady I. Padalka Gennady I. Padalka Gennady I. Padalka Flight engineer Michael R. Barratt Flight engineer Michael R. Barratt Flight engineer Michael R. Barratt Flight engineer Koichi Wakata Flight engineer Koichi Wakata Flight engineer Koichi Wakata (launched aboard STS-119, (launched aboard STS-119, (launched aboard STS-119, returned aboard STS-127) returned aboard STS-127) returned aboard STS-127) Flight engineer Timothy L. Kopra Flight engineer Timothy L. Kopra Flight engineer Timothy L. Kopra (launched aboard STS-127, (launched aboard STS-127, (launched aboard STS-127, returned aboard STS-128) returned aboard STS-128) returned aboard STS-128) Of Note: The Expedition 19 crew was Of Note: The Expedition 19 crew was Of Note: The Expedition 19 crew was joined in orbit by Russian cosmo- joined in orbit by Russian cosmo- joined in orbit by Russian cosmo- naut Roman Romanenko, ESA naut Roman Romanenko, ESA naut Roman Romanenko, ESA astronaut Frank De Winne, and astronaut Frank De Winne, and astronaut Frank De Winne, and CSA astronaut Robert Thirsk on CSA astronaut Robert Thirsk on CSA astronaut Robert Thirsk on May 29, 2009, launching aboard May 29, 2009, launching aboard May 29, 2009, launching aboard Soyuz TMA-15 from Baikonur. Their Soyuz TMA-15 from Baikonur. Their Soyuz TMA-15 from Baikonur. Their arrival inaugurated the station’s first arrival inaugurated the station’s first arrival inaugurated the station’s first six-person crew and marked the six-person crew and marked the six-person crew and marked the first time that crew members from first time that crew members from first time that crew members from all five ISS partner agencies will be all five ISS partner agencies will be all five ISS partner agencies will be living aboard at the same time. living aboard at the same time. living aboard at the same time. Returned: October 11, 2009 Returned: October 11, 2009 Returned: October 11, 2009

B-79 B-79 B-79 Expedition 20 Expedition 20 Expedition 20 Crew: ISS commander/Soyuz commander Crew: ISS commander/Soyuz commander Crew: ISS commander/Soyuz commander Gennady I. Padalka Gennady I. Padalka Gennady I. Padalka (launched March 26, 2009, aboard (launched March 26, 2009, aboard (launched March 26, 2009, aboard Soyuz TMA-14; returned Oct. 11, Soyuz TMA-14; returned Oct. 11, Soyuz TMA-14; returned Oct. 11, 2009, aboard Soyuz TMA-14) 2009, aboard Soyuz TMA-14) 2009, aboard Soyuz TMA-14) Flight engineer Michael R. Barratt Flight engineer Michael R. Barratt Flight engineer Michael R. Barratt (launched March 26, 2009, aboard (launched March 26, 2009, aboard (launched March 26, 2009, aboard Soyuz TMA-14; returned Oct. 11, Soyuz TMA-14; returned Oct. 11, Soyuz TMA-14; returned Oct. 11, 2009, aboard Soyuz TMA-14) 2009, aboard Soyuz TMA-14) 2009, aboard Soyuz TMA-14) Flight engineer Koichi Wakata Flight engineer Koichi Wakata Flight engineer Koichi Wakata (launched aboard STS-119, (launched aboard STS-119, (launched aboard STS-119, returned aboard STS-127) returned aboard STS-127) returned aboard STS-127) Flight engineer Timothy L. Kopra Flight engineer Timothy L. Kopra Flight engineer Timothy L. Kopra (launched aboard STS-127, (launched aboard STS-127, (launched aboard STS-127, returned aboard STS-128) returned aboard STS-128) returned aboard STS-128) Flight engineer Nicole Stott Flight engineer Nicole Stott Flight engineer Nicole Stott (launched aboard STS-128, (launched aboard STS-128, (launched aboard STS-128, returned aboard STS-129) returned aboard STS-129) returned aboard STS-129) Flight engineer Frank De Winne Flight engineer Frank De Winne Flight engineer Frank De Winne (launched May 27, 2009, aboard (launched May 27, 2009, aboard (launched May 27, 2009, aboard Soyuz TMA-15) Soyuz TMA-15) Soyuz TMA-15) Flight engineer Roman Romanenko Flight engineer Roman Romanenko Flight engineer Roman Romanenko (launched May 27, 2009, aboard (launched May 27, 2009, aboard (launched May 27, 2009, aboard Soyuz TMA-15) Soyuz TMA-15) Soyuz TMA-15) Flight engineer Robert Thirsk Flight engineer Robert Thirsk Flight engineer Robert Thirsk (launched May 27, 2009, aboard (launched May 27, 2009, aboard (launched May 27, 2009, aboard Soyuz TMA-15) Soyuz TMA-15) Soyuz TMA-15) Of Note: Working in spacesuits inside a Of Note: Working in spacesuits inside a Of Note: Working in spacesuits inside a compartment open to vacuum, compartment open to vacuum, compartment open to vacuum, commander Gennady Padalka and commander Gennady Padalka and commander Gennady Padalka and flight engineer Michael Barratt con- flight engineer Michael Barratt con- flight engineer Michael Barratt con- ducted a 12-minute internal space- ducted a 12-minute internal space- ducted a 12-minute internal space- walk on June 10, 2009, to finish rig- walk on June 10, 2009, to finish rig- walk on June 10, 2009, to finish rig- ging a port in the Zvezda command ging a port in the Zvezda command ging a port in the Zvezda command module for arrival of a new docking module for arrival of a new docking module for arrival of a new docking module in November. Because they module in November. Because they module in November. Because they were working in a vacuum, the ac- were working in a vacuum, the ac- were working in a vacuum, the ac- tivity was considered a spacewalk, tivity was considered a spacewalk, tivity was considered a spacewalk, the 125th since station assembly the 125th since station assembly the 125th since station assembly began in 1998. This spacewalk tied began in 1998. This spacewalk tied began in 1998. This spacewalk tied the record for the shortest EVA, a the record for the shortest EVA, a the record for the shortest EVA, a mark set in 1965 by cosmonaut mark set in 1965 by cosmonaut mark set in 1965 by cosmonaut Alexei Leonov in the first spacewalk Alexei Leonov in the first spacewalk Alexei Leonov in the first spacewalk ever conducted. ever conducted. ever conducted.

B-80 B-80 B-80 Expedition 21 Expedition 21 Expedition 21 Crew: ISS commander Frank De Winne Crew: ISS commander Frank De Winne Crew: ISS commander Frank De Winne (launched May 27, 2009, aboard (launched May 27, 2009, aboard (launched May 27, 2009, aboard Soyuz TMA-15; returned Dec. 1, Soyuz TMA-15; returned Dec. 1, Soyuz TMA-15; returned Dec. 1, 2009, aboard Soyuz TMA-15) 2009, aboard Soyuz TMA-15) 2009, aboard Soyuz TMA-15) Soyuz commander/flight engineer Soyuz commander/flight engineer Soyuz commander/flight engineer Roman Romanenko Roman Romanenko Roman Romanenko (launched May 27, 2009, aboard (launched May 27, 2009, aboard (launched May 27, 2009, aboard Soyuz TMA-15; returned Dec. 1, Soyuz TMA-15; returned Dec. 1, Soyuz TMA-15; returned Dec. 1, 2009, aboard Soyuz TMA-15) 2009, aboard Soyuz TMA-15) 2009, aboard Soyuz TMA-15) Flight engineer Robert B. Thirsk Flight engineer Robert B. Thirsk Flight engineer Robert B. Thirsk (launched May 27, 2009, aboard (launched May 27, 2009, aboard (launched May 27, 2009, aboard Soyuz TMA-15; returned Dec. 1, Soyuz TMA-15; returned Dec. 1, Soyuz TMA-15; returned Dec. 1, 2009, aboard Soyuz TMA-15) 2009, aboard Soyuz TMA-15) 2009, aboard Soyuz TMA-15) Flight engineer Nicole P. Stott Flight engineer Nicole P. Stott Flight engineer Nicole P. Stott (launched aboard STS-128, (launched aboard STS-128, (launched aboard STS-128, returned aboard STS-129) returned aboard STS-129) returned aboard STS-129) Flight engineer Jeffrey N. Williams Flight engineer Jeffrey N. Williams Flight engineer Jeffrey N. Williams (launched Sept. 30, 2009, aboard (launched Sept. 30, 2009, aboard (launched Sept. 30, 2009, aboard Soyuz TMA-16) Soyuz TMA-16) Soyuz TMA-16) Flight engineer Maxim Suraev Flight engineer Maxim Suraev Flight engineer Maxim Suraev (launched Sept. 30, 2009, aboard (launched Sept. 30, 2009, aboard (launched Sept. 30, 2009, aboard Soyuz TMA-16) Soyuz TMA-16) Soyuz TMA-16)

Expedition 22 Expedition 22 Expedition 22 Crew: ISS commander Jeffrey N. Williams Crew: ISS commander Jeffrey N. Williams Crew: ISS commander Jeffrey N. Williams (launched Sept. 30, 2009, aboard (launched Sept. 30, 2009, aboard (launched Sept. 30, 2009, aboard Soyuz TMA-16) Soyuz TMA-16) Soyuz TMA-16) Soyuz commander/flight engineer Soyuz commander/flight engineer Soyuz commander/flight engineer Maxim Suraev Maxim Suraev Maxim Suraev (launched Sept. 30, 2009, aboard (launched Sept. 30, 2009, aboard (launched Sept. 30, 2009, aboard Soyuz TMA-16) Soyuz TMA-16) Soyuz TMA-16) Flight engineer Oleg V. Kotov Flight engineer Oleg V. Kotov Flight engineer Oleg V. Kotov (launched Dec. 20, 2009, aboard (launched Dec. 20, 2009, aboard (launched Dec. 20, 2009, aboard Soyuz TMA-17) Soyuz TMA-17) Soyuz TMA-17) Flight engineer Soichi Noguchi Flight engineer Soichi Noguchi Flight engineer Soichi Noguchi (launched Dec. 20, 2009, aboard (launched Dec. 20, 2009, aboard (launched Dec. 20, 2009, aboard Soyuz TMA-17) Soyuz TMA-17) Soyuz TMA-17) Flight engineer Timothy J. Creamer Flight engineer Timothy J. Creamer Flight engineer Timothy J. Creamer (launched Dec. 20, 2009, aboard (launched Dec. 20, 2009, aboard (launched Dec. 20, 2009, aboard Soyuz TMA-17) Soyuz TMA-17) Soyuz TMA-17)

B-81 B-81 B-81 INTERESTING ISS FACTS INTERESTING ISS FACTS INTERESTING ISS FACTS

The space station runs on about 7.5 million lines of soft- The space station runs on about 7.5 million lines of soft- The space station runs on about 7.5 million lines of soft- ware code on more than 50 computers communicating ware code on more than 50 computers communicating ware code on more than 50 computers communicating via 100 data networks transferring 400,000 signals, e.g., via 100 data networks transferring 400,000 signals, e.g., via 100 data networks transferring 400,000 signals, e.g., pressure or temperature measurements, valve positions, pressure or temperature measurements, valve positions, pressure or temperature measurements, valve positions, etc. These figures do not include Microsoft Windows on etc. These figures do not include Microsoft Windows on etc. These figures do not include Microsoft Windows on station laptop computers. station laptop computers. station laptop computers. Astronauts, cosmonauts, and space flight participants Astronauts, cosmonauts, and space flight participants Astronauts, cosmonauts, and space flight participants from 15 nations have visited the International Space Station from 15 nations have visited the International Space Station from 15 nations have visited the International Space Station or lived aboard the station as Expedition crew members. or lived aboard the station as Expedition crew members. or lived aboard the station as Expedition crew members. The nations represented are the United States, Russia, The nations represented are the United States, Russia, The nations represented are the United States, Russia, Canada, Italy, France, Japan, South Africa, Belgium, Canada, Italy, France, Japan, South Africa, Belgium, Canada, Italy, France, Japan, South Africa, Belgium, Spain, the Netherlands, and Brazil. Spain, the Netherlands, and Brazil. Spain, the Netherlands, and Brazil. The ISS will be about four times as large as the Russian The ISS will be about four times as large as the Russian The ISS will be about four times as large as the Russian space station Mir and about five times as large as the space station Mir and about five times as large as the space station Mir and about five times as large as the U.S. Skylab. U.S. Skylab. U.S. Skylab. With nine rooms, two toilets, two kitchens, and two mini- With nine rooms, two toilets, two kitchens, and two mini- With nine rooms, two toilets, two kitchens, and two mini- gyms, the nearly completed ISS can comfortably accom- gyms, the nearly completed ISS can comfortably accom- gyms, the nearly completed ISS can comfortably accom- modate its six-person crew. modate its six-person crew. modate its six-person crew. Astronauts eat healthy but less tasty meals because of Astronauts eat healthy but less tasty meals because of Astronauts eat healthy but less tasty meals because of special considerations while in space. Salt, for example, special considerations while in space. Salt, for example, special considerations while in space. Salt, for example, accelerates bone loss. Vitamin D must be added because accelerates bone loss. Vitamin D must be added because accelerates bone loss. Vitamin D must be added because of the lack of sunlight. Food is usually highly seasoned of the lack of sunlight. Food is usually highly seasoned of the lack of sunlight. Food is usually highly seasoned because the sense of taste diminishes during space travel. because the sense of taste diminishes during space travel. because the sense of taste diminishes during space travel. Products must have at least a one-year shelf life and be Products must have at least a one-year shelf life and be Products must have at least a one-year shelf life and be contained in lightweight, pressure-resistant packaging. contained in lightweight, pressure-resistant packaging. contained in lightweight, pressure-resistant packaging. The ISS travels an equivalent distance to the moon and The ISS travels an equivalent distance to the moon and The ISS travels an equivalent distance to the moon and back in about a day. back in about a day. back in about a day. In a 24-hour period, the ISS orbits Earth 16 times. As of In a 24-hour period, the ISS orbits Earth 16 times. As of In a 24-hour period, the ISS orbits Earth 16 times. As of January 2010, it has circled the Earth nearly 66,000 times. January 2010, it has circled the Earth nearly 66,000 times. January 2010, it has circled the Earth nearly 66,000 times. To prepare for spacewalks, crew members train in a 6.2- To prepare for spacewalks, crew members train in a 6.2- To prepare for spacewalks, crew members train in a 6.2- million-gallon pool at the Neutral Buoyancy Laboratory million-gallon pool at the Neutral Buoyancy Laboratory million-gallon pool at the Neutral Buoyancy Laboratory (NBL) in Houston, Texas. (NBL) in Houston, Texas. (NBL) in Houston, Texas. The 55-foot station robot arm is able to lift 220,000 pounds, The 55-foot station robot arm is able to lift 220,000 pounds, The 55-foot station robot arm is able to lift 220,000 pounds, the weight of a space shuttle orbiter. the weight of a space shuttle orbiter. the weight of a space shuttle orbiter. The ISS effort involves more than 100,000 people in space The ISS effort involves more than 100,000 people in space The ISS effort involves more than 100,000 people in space agencies and at 500 contractor facilities in 37 U.S. states agencies and at 500 contractor facilities in 37 U.S. states agencies and at 500 contractor facilities in 37 U.S. states and in 16 countries. and in 16 countries. and in 16 countries. NASA has developed a video game, “Station Spacewalk,” NASA has developed a video game, “Station Spacewalk,” NASA has developed a video game, “Station Spacewalk,” to give players the virtual opportunity to experience the to give players the virtual opportunity to experience the to give players the virtual opportunity to experience the thrill of working on the ISS from their computers. This thrill of working on the ISS from their computers. This thrill of working on the ISS from their computers. This game features simulations of actual EVAs conducted game features simulations of actual EVAs conducted game features simulations of actual EVAs conducted by NASA astronauts on missions and incorporates 3D by NASA astronauts on missions and incorporates 3D by NASA astronauts on missions and incorporates 3D graphics used by the agency. Players can play the game graphics used by the agency. Players can play the game graphics used by the agency. Players can play the game in their browser, or download it for the Windows and Mac in their browser, or download it for the Windows and Mac in their browser, or download it for the Windows and Mac platforms. To take a virtual spacewalk in the “Station platforms. To take a virtual spacewalk in the “Station platforms. To take a virtual spacewalk in the “Station Spacewalk” game, visit: Spacewalk” game, visit: Spacewalk” game, visit:

http://www.nasa.gov/multimedia/3d_resources/ http://www.nasa.gov/multimedia/3d_resources/ http://www.nasa.gov/multimedia/3d_resources/ station_spacewalk_game.html station_spacewalk_game.html station_spacewalk_game.html

B-82 B-82 B-82 STS-1 Mission Facts — Columbia — STS-1 Mission Facts — Columbia — STS-1 Mission Facts — Columbia — April 12–14, 1981 April 12–14, 1981 April 12–14, 1981

Commander: John W. Young Commander: John W. Young Commander: John W. Young Pilot: Robert Crippen Pilot: Robert Crippen Pilot: Robert Crippen Mission Duration: 54 hours, 20 minutes, 32 seconds Mission Duration: 54 hours, 20 minutes, 32 seconds Mission Duration: 54 hours, 20 minutes, 32 seconds Miles Traveled: Approximately 1,074,567 statute miles Miles Traveled: Approximately 1,074,567 statute miles Miles Traveled: Approximately 1,074,567 statute miles Inclination: 40 degrees Inclination: 40 degrees Inclination: 40 degrees Orbits of Earth: 36 Orbits of Earth: 36 Orbits of Earth: 36 Orbital Altitude: 145 nautical miles (166 statute miles) Orbital Altitude: 145 nautical miles (166 statute miles) Orbital Altitude: 145 nautical miles (166 statute miles) Landing Touchdown: 6,053 feet beyond planned Landing Touchdown: 6,053 feet beyond planned Landing Touchdown: 6,053 feet beyond planned touchdown point touchdown point touchdown point Landing Rollout: 8,993 feet from main gear touchdown Landing Rollout: 8,993 feet from main gear touchdown Landing Rollout: 8,993 feet from main gear touchdown Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately 195,472 pounds 195,472 pounds 195,472 pounds Landing Speed at Main Gear Touchdown: 183 knots Landing Speed at Main Gear Touchdown: 183 knots Landing Speed at Main Gear Touchdown: 183 knots (210 mph) (210 mph) (210 mph) Lift-off Weight: Approximately 4,457,111 pounds Lift-off Weight: Approximately 4,457,111 pounds Lift-off Weight: Approximately 4,457,111 pounds Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately 219,258 pounds 219,258 pounds 219,258 pounds Cargo Weight Up and Down: Approximately Cargo Weight Up and Down: Approximately Cargo Weight Up and Down: Approximately 10,823 pounds 10,823 pounds 10,823 pounds Landed: Runway 23 dry lake bed at Edwards Air Force Landed: Runway 23 dry lake bed at Edwards Air Force Landed: Runway 23 dry lake bed at Edwards Air Force Base, California Base, California Base, California Payloads: Development Flight Instrumentation and Payloads: Development Flight Instrumentation and Payloads: Development Flight Instrumentation and Aerodynamic Coefficient Identification Package Aerodynamic Coefficient Identification Package Aerodynamic Coefficient Identification Package

STS-2 Mission Facts — Columbia — STS-2 Mission Facts — Columbia — STS-2 Mission Facts — Columbia — November 12–14, 1981 November 12–14, 1981 November 12–14, 1981

Commander: Joe Engle Commander: Joe Engle Commander: Joe Engle Pilot: Richard Truly Pilot: Richard Truly Pilot: Richard Truly Mission Duration: 54 hours, 13 minutes, 13 seconds Mission Duration: 54 hours, 13 minutes, 13 seconds Mission Duration: 54 hours, 13 minutes, 13 seconds Miles Traveled: Approximately 1,074,567 statute miles Miles Traveled: Approximately 1,074,567 statute miles Miles Traveled: Approximately 1,074,567 statute miles Inclination: 38 degrees Inclination: 38 degrees Inclination: 38 degrees Orbits of Earth: 36 Orbits of Earth: 36 Orbits of Earth: 36 Orbital Altitude: 137 nautical miles (157 statute miles) Orbital Altitude: 137 nautical miles (157 statute miles) Orbital Altitude: 137 nautical miles (157 statute miles) Landing Touchdown: Approximately 780 feet beyond Landing Touchdown: Approximately 780 feet beyond Landing Touchdown: Approximately 780 feet beyond planned touchdown point planned touchdown point planned touchdown point Landing Rollout: Approximately 7,711 feet from main Landing Rollout: Approximately 7,711 feet from main Landing Rollout: Approximately 7,711 feet from main gear touchdown gear touchdown gear touchdown Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately 204,262 pounds 204,262 pounds 204,262 pounds Landing Speed at Main Gear Touchdown: Landing Speed at Main Gear Touchdown: Landing Speed at Main Gear Touchdown: Approximately 197 knots (226 miles per hour) Approximately 197 knots (226 miles per hour) Approximately 197 knots (226 miles per hour) Lift-off Weight: Approximately 4,470,308 pounds Lift-off Weight: Approximately 4,470,308 pounds Lift-off Weight: Approximately 4,470,308 pounds Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately 230,708 pounds 230,708 pounds 230,708 pounds Cargo Weight Up and Down: Approximately Cargo Weight Up and Down: Approximately Cargo Weight Up and Down: Approximately 18,778 pounds 18,778 pounds 18,778 pounds Landed: Runway 23 dry lake bed at Edwards Air Force Landed: Runway 23 dry lake bed at Edwards Air Force Landed: Runway 23 dry lake bed at Edwards Air Force Base, California Base, California Base, California

Y-1 Y-1 Y-1 STS-2 Mission Facts (Cont) STS-2 Mission Facts (Cont) STS-2 Mission Facts (Cont)

Payloads: Office of Space and Terrestrial Applications Payloads: Office of Space and Terrestrial Applications Payloads: Office of Space and Terrestrial Applications (OSTA)-1 experiments, Orbiter Experiments (OEX) (OSTA)-1 experiments, Orbiter Experiments (OEX) (OSTA)-1 experiments, Orbiter Experiments (OEX)

STS-3 Mission Facts — Columbia — STS-3 Mission Facts — Columbia — STS-3 Mission Facts — Columbia — March 22–30, 1982 March 22–30, 1982 March 22–30, 1982 Commander: Jack Lousma Commander: Jack Lousma Commander: Jack Lousma Pilot: Gordon Fullerton Pilot: Gordon Fullerton Pilot: Gordon Fullerton Mission Duration: 192 hours (8 days), 4 minutes, Mission Duration: 192 hours (8 days), 4 minutes, Mission Duration: 192 hours (8 days), 4 minutes, 45 seconds 45 seconds 45 seconds Miles Traveled: Approximately 4.4 million miles Miles Traveled: Approximately 4.4 million miles Miles Traveled: Approximately 4.4 million miles Inclination: 38 degrees Inclination: 38 degrees Inclination: 38 degrees Orbits of Earth: 129 Orbits of Earth: 129 Orbits of Earth: 129 Orbital Altitude: 128 nautical miles (147 statute miles) Orbital Altitude: 128 nautical miles (147 statute miles) Orbital Altitude: 128 nautical miles (147 statute miles) Landing Touchdown: Approximately 1,092 feet from Landing Touchdown: Approximately 1,092 feet from Landing Touchdown: Approximately 1,092 feet from threshold threshold threshold Landing Rollout: Approximately 13,737 feet from main Landing Rollout: Approximately 13,737 feet from main Landing Rollout: Approximately 13,737 feet from main gear touchdown gear touchdown gear touchdown Orbiter Weight at Landing: Approximately 207,072 Orbiter Weight at Landing: Approximately 207,072 Orbiter Weight at Landing: Approximately 207,072 pounds pounds pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 220 knots (253 miles per hour) mately 220 knots (253 miles per hour) mately 220 knots (253 miles per hour) Lift-off Weight: Approximately 4,468,755 pounds Lift-off Weight: Approximately 4,468,755 pounds Lift-off Weight: Approximately 4,468,755 pounds Orbiter Weight at Lift-off: Approximately 235,415 Orbiter Weight at Lift-off: Approximately 235,415 Orbiter Weight at Lift-off: Approximately 235,415 pounds pounds pounds Cargo Weight Up and Down: Approximately 22,710 Cargo Weight Up and Down: Approximately 22,710 Cargo Weight Up and Down: Approximately 22,710 pounds pounds pounds Landed: Runway 17 dry lake bed at White Sands Missile Landed: Runway 17 dry lake bed at White Sands Missile Landed: Runway 17 dry lake bed at White Sands Missile Range, New Mexico Range, New Mexico Range, New Mexico Payloads: Office of Space Science (OSS) experiments, Payloads: Office of Space Science (OSS) experiments, Payloads: Office of Space Science (OSS) experiments, Monodisperse Latex Reactor (MLR), Electrophore- Monodisperse Latex Reactor (MLR), Electrophore- Monodisperse Latex Reactor (MLR), Electrophore- sis Verification Test (EEVT), Plant Lignification sis Verification Test (EEVT), Plant Lignification sis Verification Test (EEVT), Plant Lignification Experiment Experiment Experiment

STS-4 Mission Facts — Columbia — STS-4 Mission Facts — Columbia — STS-4 Mission Facts — Columbia — June 27–July 4, 1982 June 27–July 4, 1982 June 27–July 4, 1982

Commander: Ken Mattingly Commander: Ken Mattingly Commander: Ken Mattingly Pilot: Henry Hartsfield Pilot: Henry Hartsfield Pilot: Henry Hartsfield Mission Duration: 168 hours (7 days), 1 hour, 9 minutes, Mission Duration: 168 hours (7 days), 1 hour, 9 minutes, Mission Duration: 168 hours (7 days), 1 hour, 9 minutes, 40 seconds 40 seconds 40 seconds Miles Traveled: Approximately 3.3 million statute miles Miles Traveled: Approximately 3.3 million statute miles Miles Traveled: Approximately 3.3 million statute miles Inclination: 28.45 degrees Inclination: 28.45 degrees Inclination: 28.45 degrees Orbits of Earth: 112 Orbits of Earth: 112 Orbits of Earth: 112 Orbital Altitude: 160 nautical miles (184 statute miles), Orbital Altitude: 160 nautical miles (184 statute miles), Orbital Altitude: 160 nautical miles (184 statute miles), then to 172 nautical miles (197 statute miles) then to 172 nautical miles (197 statute miles) then to 172 nautical miles (197 statute miles) Landing Touchdown: Approximately 948 feet from Landing Touchdown: Approximately 948 feet from Landing Touchdown: Approximately 948 feet from threshold threshold threshold Landing Rollout: Approximately 9,878 feet from main Landing Rollout: Approximately 9,878 feet from main Landing Rollout: Approximately 9,878 feet from main gear touchdown gear touchdown gear touchdown

Y-2 Y-2 Y-2 STS-4 Mission Facts (Cont) STS-4 Mission Facts (Cont) STS-4 Mission Facts (Cont) Orbiter Weight at Landing: Approximately 208,946 Orbiter Weight at Landing: Approximately 208,946 Orbiter Weight at Landing: Approximately 208,946 pounds pounds pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 204 knots (234 miles per hour) mately 204 knots (234 miles per hour) mately 204 knots (234 miles per hour) Lift-off Weight: Approximately 4,481,935 pounds Lift-off Weight: Approximately 4,481,935 pounds Lift-off Weight: Approximately 4,481,935 pounds Orbiter Weight at Lift-off: Approximately 241,664 Orbiter Weight at Lift-off: Approximately 241,664 Orbiter Weight at Lift-off: Approximately 241,664 pounds pounds pounds Cargo Weight Up and Down: Approximately 24,492 Cargo Weight Up and Down: Approximately 24,492 Cargo Weight Up and Down: Approximately 24,492 pounds pounds pounds Landed: Concrete runway 22 at Edwards Air Force Landed: Concrete runway 22 at Edwards Air Force Landed: Concrete runway 22 at Edwards Air Force Base, California Base, California Base, California Payloads: Induced Environment Contamination Moni- Payloads: Induced Environment Contamination Moni- Payloads: Induced Environment Contamination Moni- tor (IECM), Monodisperse Latex Reactor (MLR), tor (IECM), Monodisperse Latex Reactor (MLR), tor (IECM), Monodisperse Latex Reactor (MLR), Continuous Flow Electrophoresis System (CFES), Continuous Flow Electrophoresis System (CFES), Continuous Flow Electrophoresis System (CFES), Development Flight Instrumentation (DFl), Orbiter Development Flight Instrumentation (DFl), Orbiter Development Flight Instrumentation (DFl), Orbiter Experiments (OEX), first NASA getaway special Experiments (OEX), first NASA getaway special Experiments (OEX), first NASA getaway special (GAS), Night/Day Optical Survey of Lightning (GAS), Night/Day Optical Survey of Lightning (GAS), Night/Day Optical Survey of Lightning (NOSL) experiment, Vapor Phase Compression (NOSL) experiment, Vapor Phase Compression (NOSL) experiment, Vapor Phase Compression (VPC) freezer heat exchanger dynamics for freez- (VPC) freezer heat exchanger dynamics for freez- (VPC) freezer heat exchanger dynamics for freez- ing samples, Aerodynamic Coefficient Identifica- ing samples, Aerodynamic Coefficient Identifica- ing samples, Aerodynamic Coefficient Identifica- tion Package (AClP) experiment tion Package (AClP) experiment tion Package (AClP) experiment

STS-5 Mission Facts — Columbia — STS-5 Mission Facts — Columbia — STS-5 Mission Facts — Columbia — November 11–16, 1982 November 11–16, 1982 November 11–16, 1982

Commander: Vance D. Brand Commander: Vance D. Brand Commander: Vance D. Brand Pilot: Robert F. Overmyer Pilot: Robert F. Overmyer Pilot: Robert F. Overmyer Mission Specialist: Joseph P. Allen Mission Specialist: Joseph P. Allen Mission Specialist: Joseph P. Allen Mission Specialist: William B. Lenoir Mission Specialist: William B. Lenoir Mission Specialist: William B. Lenoir Mission Duration: 120 hours (5 days), 2 hours, Mission Duration: 120 hours (5 days), 2 hours, Mission Duration: 120 hours (5 days), 2 hours, 14 minutes, 26 seconds 14 minutes, 26 seconds 14 minutes, 26 seconds Miles Traveled: 2,110,849 statute miles Miles Traveled: 2,110,849 statute miles Miles Traveled: 2,110,849 statute miles Inclination: 28.45 degrees Inclination: 28.45 degrees Inclination: 28.45 degrees Orbits of Earth: 81 Orbits of Earth: 81 Orbits of Earth: 81 Orbital Altitude: 160 nautical miles (184 statute miles) Orbital Altitude: 160 nautical miles (184 statute miles) Orbital Altitude: 160 nautical miles (184 statute miles) Landing Touchdown: Approximately 1,637 feet from Landing Touchdown: Approximately 1,637 feet from Landing Touchdown: Approximately 1,637 feet from threshold threshold threshold Landing Rollout: Approximately 9,553 feet from main Landing Rollout: Approximately 9,553 feet from main Landing Rollout: Approximately 9,553 feet from main gear touchdown gear touchdown gear touchdown Orbiter Weight at Landing: 202,480 pounds Orbiter Weight at Landing: 202,480 pounds Orbiter Weight at Landing: 202,480 pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 198 knots (227 miles per hour) mately 198 knots (227 miles per hour) mately 198 knots (227 miles per hour) Lift-off Weight: Approximately 4,487,268 pounds Lift-off Weight: Approximately 4,487,268 pounds Lift-off Weight: Approximately 4,487,268 pounds Orbiter Weight at Lift-off: Approximately 247,113 Orbiter Weight at Lift-off: Approximately 247,113 Orbiter Weight at Lift-off: Approximately 247,113 pounds pounds pounds Cargo Weight Up: Approximately 32,080 pounds Cargo Weight Up: Approximately 32,080 pounds Cargo Weight Up: Approximately 32,080 pounds Cargo Weight Down: Approximately 17,495 pounds Cargo Weight Down: Approximately 17,495 pounds Cargo Weight Down: Approximately 17,495 pounds Landed: Concrete runway 22 at Edwards Air Force Landed: Concrete runway 22 at Edwards Air Force Landed: Concrete runway 22 at Edwards Air Force Base, California Base, California Base, California Payloads: First mission to deploy commercial Payloads: First mission to deploy commercial Payloads: First mission to deploy commercial communications satellites: Satellite Business communications satellites: Satellite Business communications satellites: Satellite Business Systems (SBS)-C with Payload Assist Module Systems (SBS)-C with Payload Assist Module Systems (SBS)-C with Payload Assist Module

Y-3 Y-3 Y-3 STS-5 Mission Facts (Cont) STS-5 Mission Facts (Cont) STS-5 Mission Facts (Cont)

(PAM)-D; Telesat-E (Canadian communications (PAM)-D; Telesat-E (Canadian communications (PAM)-D; Telesat-E (Canadian communications satellite) with PAM-D. Monodisperse Latex Reactor satellite) with PAM-D. Monodisperse Latex Reactor satellite) with PAM-D. Monodisperse Latex Reactor (MLR), Continuous Flow Electrophoresis System (MLR), Continuous Flow Electrophoresis System (MLR), Continuous Flow Electrophoresis System (CFES), three getaway specials (GAS), Student (CFES), three getaway specials (GAS), Student (CFES), three getaway specials (GAS), Student experiments, GLOW experiment, Vestibular experi- experiments, GLOW experiment, Vestibular experi- experiments, GLOW experiment, Vestibular experi- ment, Oxygen Interaction With Materials experi- ment, Oxygen Interaction With Materials experi- ment, Oxygen Interaction With Materials experi- ment ment ment STS-6 Mission Facts — Challenger — STS-6 Mission Facts — Challenger — STS-6 Mission Facts — Challenger — April 4–9, 1983 April 4–9, 1983 April 4–9, 1983

Commander: Paul Weitz Commander: Paul Weitz Commander: Paul Weitz Pilot: Karol Bobko Pilot: Karol Bobko Pilot: Karol Bobko Mission Specialist: Donald Peterson Mission Specialist: Donald Peterson Mission Specialist: Donald Peterson Mission Specialist: Story Musgrave Mission Specialist: Story Musgrave Mission Specialist: Story Musgrave Mission Duration: 120 hours (5 days), 23 minutes, 42 Mission Duration: 120 hours (5 days), 23 minutes, 42 Mission Duration: 120 hours (5 days), 23 minutes, 42 seconds seconds seconds Miles Traveled: 2,094,293 statute miles Miles Traveled: 2,094,293 statute miles Miles Traveled: 2,094,293 statute miles Inclination: 28.45 degrees Inclination: 28.45 degrees Inclination: 28.45 degrees Orbits of Earth: 80 Orbits of Earth: 80 Orbits of Earth: 80 Orbital Altitude: 155 nautical miles (178 statute miles) Orbital Altitude: 155 nautical miles (178 statute miles) Orbital Altitude: 155 nautical miles (178 statute miles) Extravehicular Activity: Story Musgrave and Donald Extravehicular Activity: Story Musgrave and Donald Extravehicular Activity: Story Musgrave and Donald Peterson, duration 3 hours and 54 minutes Peterson, duration 3 hours and 54 minutes Peterson, duration 3 hours and 54 minutes Landing Touchdown: Approximately 2,026 feet beyond Landing Touchdown: Approximately 2,026 feet beyond Landing Touchdown: Approximately 2,026 feet beyond threshold threshold threshold Landing Rollout: Approximately 7,180 feet from main Landing Rollout: Approximately 7,180 feet from main Landing Rollout: Approximately 7,180 feet from main gear touchdown gear touchdown gear touchdown Orbiter Weight at Landing: Approximately 190,330 Orbiter Weight at Landing: Approximately 190,330 Orbiter Weight at Landing: Approximately 190,330 pounds pounds pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 190 knots (218 miles per hour) mately 190 knots (218 miles per hour) mately 190 knots (218 miles per hour) Lift-off Weight: Approximately 4,487,255 pounds Lift-off Weight: Approximately 4,487,255 pounds Lift-off Weight: Approximately 4,487,255 pounds Orbiter Weight at Lift-off: Approximately 256,744 Orbiter Weight at Lift-off: Approximately 256,744 Orbiter Weight at Lift-off: Approximately 256,744 pounds pounds pounds Cargo Weight Up: Approximately 46,971 pounds Cargo Weight Up: Approximately 46,971 pounds Cargo Weight Up: Approximately 46,971 pounds Cargo Weight Down: Approximately 9,425 pounds Cargo Weight Down: Approximately 9,425 pounds Cargo Weight Down: Approximately 9,425 pounds Landed: Concrete runway 22 at Edwards Air Force Landed: Concrete runway 22 at Edwards Air Force Landed: Concrete runway 22 at Edwards Air Force Base, California Base, California Base, California Payloads: Deployment of Tracking and Data Relay Sat- Payloads: Deployment of Tracking and Data Relay Sat- Payloads: Deployment of Tracking and Data Relay Sat- ellite (TDRS)-A with Inertial Upper Stage (lUS)-2, ellite (TDRS)-A with Inertial Upper Stage (lUS)-2, ellite (TDRS)-A with Inertial Upper Stage (lUS)-2, Continuous Flow Electrophoresis System (CFES), Continuous Flow Electrophoresis System (CFES), Continuous Flow Electrophoresis System (CFES), Monodisperse Latex Reactor (MLR), Night/Day Monodisperse Latex Reactor (MLR), Night/Day Monodisperse Latex Reactor (MLR), Night/Day Optical Survey of Lightning (NOSL) experiment, Optical Survey of Lightning (NOSL) experiment, Optical Survey of Lightning (NOSL) experiment, three getaway specials (GAS) three getaway specials (GAS) three getaway specials (GAS)

STS-7 Mission Facts — Challenger — STS-7 Mission Facts — Challenger — STS-7 Mission Facts — Challenger — June 18–24, 1983 June 18–24, 1983 June 18–24, 1983

Commander: Robert L. Crippen Commander: Robert L. Crippen Commander: Robert L. Crippen Pilot: Frederick H. Hauck Pilot: Frederick H. Hauck Pilot: Frederick H. Hauck Mission Specialist: Sally K. Ride Mission Specialist: Sally K. Ride Mission Specialist: Sally K. Ride

Y-4 Y-4 Y-4 STS-7 Mission Facts (Cont) STS-7 Mission Facts (Cont) STS-7 Mission Facts (Cont)

Mission Specialist: John M. Fabian Mission Specialist: John M. Fabian Mission Specialist: John M. Fabian Mission Specialist: Norman E. Thagard Mission Specialist: Norman E. Thagard Mission Specialist: Norman E. Thagard Mission Duration: 144 hours (6 days), 2 hours, Mission Duration: 144 hours (6 days), 2 hours, Mission Duration: 144 hours (6 days), 2 hours, 23 minutes, 59 seconds 23 minutes, 59 seconds 23 minutes, 59 seconds Miles Traveled: 2,530,567 statute miles Miles Traveled: 2,530,567 statute miles Miles Traveled: 2,530,567 statute miles Inclination: 28.45 degrees Inclination: 28.45 degrees Inclination: 28.45 degrees Orbits of Earth: 97 Orbits of Earth: 97 Orbits of Earth: 97 Orbital Altitude: 160 nautical miles (184 statute miles) Orbital Altitude: 160 nautical miles (184 statute miles) Orbital Altitude: 160 nautical miles (184 statute miles) to 160 by 165 nautical miles (184 by 189 statute to 160 by 165 nautical miles (184 by 189 statute to 160 by 165 nautical miles (184 by 189 statute miles) to 160 by 170 nautical miles (184 by 195 miles) to 160 by 170 nautical miles (184 by 195 miles) to 160 by 170 nautical miles (184 by 195 statute miles) to 157 by 170 nautical miles (180 by statute miles) to 157 by 170 nautical miles (180 by statute miles) to 157 by 170 nautical miles (180 by 195 statute miles) to 157 nautical miles 195 statute miles) to 157 nautical miles 195 statute miles) to 157 nautical miles (180 statute miles) (180 statute miles) (180 statute miles) Landing Touchdown: Approximately 2,726 feet beyond Landing Touchdown: Approximately 2,726 feet beyond Landing Touchdown: Approximately 2,726 feet beyond threshold threshold threshold Landing Rollout: Approximately 10,450 feet from main Landing Rollout: Approximately 10,450 feet from main Landing Rollout: Approximately 10,450 feet from main gear touchdown gear touchdown gear touchdown Orbiter Weight at Landing: Approximately 204,043 Orbiter Weight at Landing: Approximately 204,043 Orbiter Weight at Landing: Approximately 204,043 pounds pounds pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 202 knots (232 miles per hour) mately 202 knots (232 miles per hour) mately 202 knots (232 miles per hour) Lift-off Weight: Approximately 4,482,241 pounds Lift-off Weight: Approximately 4,482,241 pounds Lift-off Weight: Approximately 4,482,241 pounds Orbiter Weight at Lift-off: Approximately 249,178 Orbiter Weight at Lift-off: Approximately 249,178 Orbiter Weight at Lift-off: Approximately 249,178 pounds pounds pounds Cargo Weight Up: Approximately 37,124 pounds Cargo Weight Up: Approximately 37,124 pounds Cargo Weight Up: Approximately 37,124 pounds Cargo Weight Down: Approximately 22,175 pounds Cargo Weight Down: Approximately 22,175 pounds Cargo Weight Down: Approximately 22,175 pounds Landed: Runway 15 dry lake bed at Edwards Air Force Landed: Runway 15 dry lake bed at Edwards Air Force Landed: Runway 15 dry lake bed at Edwards Air Force Base, California Base, California Base, California Payloads: Office of Space and Terrestrial Applications Payloads: Office of Space and Terrestrial Applications Payloads: Office of Space and Terrestrial Applications (OSTA)-2 experiments, deployment of PALAPA- (OSTA)-2 experiments, deployment of PALAPA- (OSTA)-2 experiments, deployment of PALAPA- B1 communications satellite for Indonesia with B1 communications satellite for Indonesia with B1 communications satellite for Indonesia with Payload Assist Module (PAM)-D and Telesat-F Payload Assist Module (PAM)-D and Telesat-F Payload Assist Module (PAM)-D and Telesat-F communications satellite for Canada with communications satellite for Canada with communications satellite for Canada with PAM-D, German Shuttle Pallet Satellite PAM-D, German Shuttle Pallet Satellite PAM-D, German Shuttle Pallet Satellite (SPAS)-01, seven getaway specials (GAS), Mono- (SPAS)-01, seven getaway specials (GAS), Mono- (SPAS)-01, seven getaway specials (GAS), Mono- disperse Latex Reactor (MLR), Continuous Flow disperse Latex Reactor (MLR), Continuous Flow disperse Latex Reactor (MLR), Continuous Flow Electrophoresis System (CFES) Electrophoresis System (CFES) Electrophoresis System (CFES)

STS-8 Mission Facts — Challenger — STS-8 Mission Facts — Challenger — STS-8 Mission Facts — Challenger — August 30–September 5, 1983 August 30–September 5, 1983 August 30–September 5, 1983

Commander: Richard H. Truly Commander: Richard H. Truly Commander: Richard H. Truly Pilot: Daniel C. Brandenstein Pilot: Daniel C. Brandenstein Pilot: Daniel C. Brandenstein Mission Specialist: Guion S. Bluford, Jr. Mission Specialist: Guion S. Bluford, Jr. Mission Specialist: Guion S. Bluford, Jr. Mission Specialist: Dale A. Gardner Mission Specialist: Dale A. Gardner Mission Specialist: Dale A. Gardner Mission Specialist: William E. Thornton Mission Specialist: William E. Thornton Mission Specialist: William E. Thornton Mission Duration: 144 hours (6 days), 1 hour, 8 minutes, Mission Duration: 144 hours (6 days), 1 hour, 8 minutes, Mission Duration: 144 hours (6 days), 1 hour, 8 minutes, 43 seconds 43 seconds 43 seconds Miles Traveled: 2,514,478 statute miles Miles Traveled: 2,514,478 statute miles Miles Traveled: 2,514,478 statute miles Inclination: 28.45 degrees Inclination: 28.45 degrees Inclination: 28.45 degrees Orbits of Earth: 97 Orbits of Earth: 97 Orbits of Earth: 97

Y-5 Y-5 Y-5 STS-8 Mission Facts (Cont) STS-8 Mission Facts (Cont) STS-8 Mission Facts (Cont)

Orbital Altitude: 160 nautical miles (184 statute miles) Orbital Altitude: 160 nautical miles (184 statute miles) Orbital Altitude: 160 nautical miles (184 statute miles) to 166 by 160 nautical miles (191 by 184 statute to 166 by 160 nautical miles (191 by 184 statute to 166 by 160 nautical miles (191 by 184 statute miles) to 166 by 121 nautical miles (191 by 139 miles) to 166 by 121 nautical miles (191 by 139 miles) to 166 by 121 nautical miles (191 by 139 statute miles) to 121 nautical miles (139 statute statute miles) to 121 nautical miles (139 statute statute miles) to 121 nautical miles (139 statute miles) miles) miles) Landing Touchdown: Approximately 2,793 feet beyond Landing Touchdown: Approximately 2,793 feet beyond Landing Touchdown: Approximately 2,793 feet beyond threshold threshold threshold Landing Rollout: Approximately 9,371 feet from main Landing Rollout: Approximately 9,371 feet from main Landing Rollout: Approximately 9,371 feet from main gear touchdown gear touchdown gear touchdown Orbiter Weight at Landing: Approximately 203,945 Orbiter Weight at Landing: Approximately 203,945 Orbiter Weight at Landing: Approximately 203,945 pounds pounds pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 195 knots (224 miles per hour) mately 195 knots (224 miles per hour) mately 195 knots (224 miles per hour) Lift-off Weight: Approximately 4,492,074 pounds Lift-off Weight: Approximately 4,492,074 pounds Lift-off Weight: Approximately 4,492,074 pounds Orbiter Weight at Lift-off: Approximately 242,742 Orbiter Weight at Lift-off: Approximately 242,742 Orbiter Weight at Lift-off: Approximately 242,742 pounds pounds pounds Cargo Weight Up: Approximately 30,076 pounds Cargo Weight Up: Approximately 30,076 pounds Cargo Weight Up: Approximately 30,076 pounds Cargo Weight Down: Approximately 22,631 pounds Cargo Weight Down: Approximately 22,631 pounds Cargo Weight Down: Approximately 22,631 pounds Landed: Concrete runway 22 at Edwards Air Force Landed: Concrete runway 22 at Edwards Air Force Landed: Concrete runway 22 at Edwards Air Force Base, California Base, California Base, California First night launch and night landing First night launch and night landing First night launch and night landing Payloads: Deployment of INSAT (lndia communica- Payloads: Deployment of INSAT (lndia communica- Payloads: Deployment of INSAT (lndia communica- tion satellite) with Payload Assist Module (PAM)-D, tion satellite) with Payload Assist Module (PAM)-D, tion satellite) with Payload Assist Module (PAM)-D, Payload Flight Test Article (PFTA)/ Payload Flight Test Article (PFTA)/ Payload Flight Test Article (PFTA)/ Payload Deployment Retrieval System (PDRS), Payload Deployment Retrieval System (PDRS), Payload Deployment Retrieval System (PDRS), Continuous Flow Electrophoresis (CFES), biomedi- Continuous Flow Electrophoresis (CFES), biomedi- Continuous Flow Electrophoresis (CFES), biomedi- cal experiments. 250,000 express mail envelopes cal experiments. 250,000 express mail envelopes cal experiments. 250,000 express mail envelopes with special cachet for U.S. Postal Service were with special cachet for U.S. Postal Service were with special cachet for U.S. Postal Service were carried for a first-day cover. carried for a first-day cover. carried for a first-day cover.

STS-9 Mission Facts — Columbia — STS-9 Mission Facts — Columbia — STS-9 Mission Facts — Columbia — November 28–December 8, 1983 November 28–December 8, 1983 November 28–December 8, 1983

Commander: John Young Commander: John Young Commander: John Young Pilot: Brewster Shaw Pilot: Brewster Shaw Pilot: Brewster Shaw Mission Specialist: Robert Parker Mission Specialist: Robert Parker Mission Specialist: Robert Parker Mission Specialist: Owen Garriott Mission Specialist: Owen Garriott Mission Specialist: Owen Garriott Payload Specialist: Byron Lichtenberg Payload Specialist: Byron Lichtenberg Payload Specialist: Byron Lichtenberg Payload Specialist: Ulf Merbold Payload Specialist: Ulf Merbold Payload Specialist: Ulf Merbold Mission Duration: 240 hours (10 days), 7 hours, Mission Duration: 240 hours (10 days), 7 hours, Mission Duration: 240 hours (10 days), 7 hours, 47 minutes, 24 seconds 47 minutes, 24 seconds 47 minutes, 24 seconds Miles Traveled: 4,295,853 statute miles Miles Traveled: 4,295,853 statute miles Miles Traveled: 4,295,853 statute miles Inclination: 57 degrees Inclination: 57 degrees Inclination: 57 degrees Orbits of Earth: 166 Orbits of Earth: 166 Orbits of Earth: 166 Orbital Altitude: 135 nautical miles (155 statute miles) Orbital Altitude: 135 nautical miles (155 statute miles) Orbital Altitude: 135 nautical miles (155 statute miles) Landing Touchdown: Approximately 1,649 feet beyond Landing Touchdown: Approximately 1,649 feet beyond Landing Touchdown: Approximately 1,649 feet beyond planned touchdown point planned touchdown point planned touchdown point Landing Rollout: Approximately 8,456 feet from main Landing Rollout: Approximately 8,456 feet from main Landing Rollout: Approximately 8,456 feet from main gear touchdown gear touchdown gear touchdown Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately 220,027 pounds 220,027 pounds 220,027 pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 185 knots (212 miles per hour) mately 185 knots (212 miles per hour) mately 185 knots (212 miles per hour) Y-6 Y-6 Y-6 STS-9 Mission Facts (Cont) STS-9 Mission Facts (Cont) STS-9 Mission Facts (Cont)

Lift-off Weight: Approximately 4,503,361 pounds Lift-off Weight: Approximately 4,503,361 pounds Lift-off Weight: Approximately 4,503,361 pounds Orbiter Weight at Lift-off: Approximately 247,619 Orbiter Weight at Lift-off: Approximately 247,619 Orbiter Weight at Lift-off: Approximately 247,619 pounds pounds pounds Cargo Weight Up and Down: Approximately 33,264 Cargo Weight Up and Down: Approximately 33,264 Cargo Weight Up and Down: Approximately 33,264 pounds pounds pounds Landed: Runway 17 dry lake bed at Edwards Air Force Landed: Runway 17 dry lake bed at Edwards Air Force Landed: Runway 17 dry lake bed at Edwards Air Force Base, California Base, California Base, California Payload: Spacelab-1 experiments, habitable Spacelab Payload: Spacelab-1 experiments, habitable Spacelab Payload: Spacelab-1 experiments, habitable Spacelab and pallet, carried 71 experiments. The six-man and pallet, carried 71 experiments. The six-man and pallet, carried 71 experiments. The six-man crew was divided into two 12-hour-day red and crew was divided into two 12-hour-day red and crew was divided into two 12-hour-day red and blue teams to operate experiments. First high- blue teams to operate experiments. First high- blue teams to operate experiments. First high- inclination orbit of 57 degrees. inclination orbit of 57 degrees. inclination orbit of 57 degrees.

41-B Mission Facts — Challenger — 41-B Mission Facts — Challenger — 41-B Mission Facts — Challenger — February 3–11, 1984 February 3–11, 1984 February 3–11, 1984

Commander: Vance Brand Commander: Vance Brand Commander: Vance Brand Pilot: Robert Gibson Pilot: Robert Gibson Pilot: Robert Gibson Mission Specialist: Bruce McCandless Mission Specialist: Bruce McCandless Mission Specialist: Bruce McCandless Mission Specialist: Robert Stewart Mission Specialist: Robert Stewart Mission Specialist: Robert Stewart Mission Specialist: Ronald McNair Mission Specialist: Ronald McNair Mission Specialist: Ronald McNair Mission Duration: 168 hours (7 days), 23 hours, 15 Mission Duration: 168 hours (7 days), 23 hours, 15 Mission Duration: 168 hours (7 days), 23 hours, 15 minutes, 55 seconds minutes, 55 seconds minutes, 55 seconds Miles Traveled: Approximately 3,311,379 statute miles Miles Traveled: Approximately 3,311,379 statute miles Miles Traveled: Approximately 3,311,379 statute miles Inclination: 28.45 degrees Inclination: 28.45 degrees Inclination: 28.45 degrees Orbits of Earth: 127 Orbits of Earth: 127 Orbits of Earth: 127 Orbital Altitude: 165 nautical miles (189 statute miles), Orbital Altitude: 165 nautical miles (189 statute miles), Orbital Altitude: 165 nautical miles (189 statute miles), then to 170 by 165 nautical miles (195 by 189 stat- then to 170 by 165 nautical miles (195 by 189 stat- then to 170 by 165 nautical miles (195 by 189 stat- ute miles), then to 176 by 165 nautical miles (202 ute miles), then to 176 by 165 nautical miles (202 ute miles), then to 176 by 165 nautical miles (202 by 189 statute miles), then to 176 by 155 nautical by 189 statute miles), then to 176 by 155 nautical by 189 statute miles), then to 176 by 155 nautical miles (202 by 178 statute miles), then to 155 by 155 miles (202 by 178 statute miles), then to 155 by 155 miles (202 by 178 statute miles), then to 155 by 155 nautical miles (178 by 178 statute miles), then to nautical miles (178 by 178 statute miles), then to nautical miles (178 by 178 statute miles), then to 152 by 152 nautical miles (174 by 174 statute miles) 152 by 152 nautical miles (174 by 174 statute miles) 152 by 152 nautical miles (174 by 174 statute miles) Extravehicular Activity (EVA): Bruce McCandless and Extravehicular Activity (EVA): Bruce McCandless and Extravehicular Activity (EVA): Bruce McCandless and Robert Stewart. EVA No. 1 duration 5 hours, 35 Robert Stewart. EVA No. 1 duration 5 hours, 35 Robert Stewart. EVA No. 1 duration 5 hours, 35 minutes, EVA No. 2 duration 6 hours, 2 minutes. minutes, EVA No. 2 duration 6 hours, 2 minutes. minutes, EVA No. 2 duration 6 hours, 2 minutes. First flight of the manned maneuvering unit (MMU). First flight of the manned maneuvering unit (MMU). First flight of the manned maneuvering unit (MMU). Bruce McCandless operating time one hour, Bruce McCandless operating time one hour, Bruce McCandless operating time one hour, 55 minutes; Robert Stewart, 44 minutes 55 minutes; Robert Stewart, 44 minutes 55 minutes; Robert Stewart, 44 minutes Landing Touchdown: Approximately 1,922 feet beyond Landing Touchdown: Approximately 1,922 feet beyond Landing Touchdown: Approximately 1,922 feet beyond runway threshold runway threshold runway threshold Landing Rollout: Approximately 10,815 feet from main Landing Rollout: Approximately 10,815 feet from main Landing Rollout: Approximately 10,815 feet from main gear touchdown gear touchdown gear touchdown Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately 201,238 pounds 201,238 pounds 201,238 pounds Lift-off Weight: Approximately 4,498,443 pounds Lift-off Weight: Approximately 4,498,443 pounds Lift-off Weight: Approximately 4,498,443 pounds Orbiter Weight at Lift-off: Approximately 250,285 Orbiter Weight at Lift-off: Approximately 250,285 Orbiter Weight at Lift-off: Approximately 250,285 pounds pounds pounds Landing Speed at Main Gear Touchdown: Landing Speed at Main Gear Touchdown: Landing Speed at Main Gear Touchdown: Approximately 196 knots (225 miles per hour) Approximately 196 knots (225 miles per hour) Approximately 196 knots (225 miles per hour) Cargo Weight Up: Approximately 33,868 pounds Cargo Weight Up: Approximately 33,868 pounds Cargo Weight Up: Approximately 33,868 pounds

Y-7 Y-7 Y-7 41-B Mission Facts (Cont) 41-B Mission Facts (Cont) 41-B Mission Facts (Cont)

Cargo Weight Down: Approximately 19,005 pounds Cargo Weight Down: Approximately 19,005 pounds Cargo Weight Down: Approximately 19,005 pounds Landed: Runway 15 at Kennedy Space Center, Florida Landed: Runway 15 at Kennedy Space Center, Florida Landed: Runway 15 at Kennedy Space Center, Florida Payloads: PALAPA-B2 (Indonesian communications Payloads: PALAPA-B2 (Indonesian communications Payloads: PALAPA-B2 (Indonesian communications satellite) with Payload Assist Module (PAM)-D satellite) with Payload Assist Module (PAM)-D satellite) with Payload Assist Module (PAM)-D and WESTAR (Western Union communications and WESTAR (Western Union communications and WESTAR (Western Union communications satellite)-Vl with PAM-D deployment. Both satellites satellite)-Vl with PAM-D deployment. Both satellites satellite)-Vl with PAM-D deployment. Both satellites were deployed but the PAM-D in each satellite were deployed but the PAM-D in each satellite were deployed but the PAM-D in each satellite failed to ignite, leaving both satellites in earth failed to ignite, leaving both satellites in earth failed to ignite, leaving both satellites in earth orbit. Both satellites were retrieved and returned orbit. Both satellites were retrieved and returned orbit. Both satellites were retrieved and returned to earth for renovation on the STS-51-A mission. to earth for renovation on the STS-51-A mission. to earth for renovation on the STS-51-A mission. The manned maneuvering unit (MMU) was tested The manned maneuvering unit (MMU) was tested The manned maneuvering unit (MMU) was tested with extravehicular astronauts as free flyers without with extravehicular astronauts as free flyers without with extravehicular astronauts as free flyers without tethers as far as 320 feet from the orbiter. Shuttle tethers as far as 320 feet from the orbiter. Shuttle tethers as far as 320 feet from the orbiter. Shuttle Pallet Satellite (SPAS)-01 experiments, Monodis- Pallet Satellite (SPAS)-01 experiments, Monodis- Pallet Satellite (SPAS)-01 experiments, Monodis- perse Latex Reactor (MLR), Isoelectric Focusing perse Latex Reactor (MLR), Isoelectric Focusing perse Latex Reactor (MLR), Isoelectric Focusing Experiment (lEF), Acoustic Containerless Experi- Experiment (lEF), Acoustic Containerless Experi- Experiment (lEF), Acoustic Containerless Experi- ment System (ACES), Cinema 360 cameras, five ment System (ACES), Cinema 360 cameras, five ment System (ACES), Cinema 360 cameras, five getaway specials (GAS), Aerodynamic Coefficient getaway specials (GAS), Aerodynamic Coefficient getaway specials (GAS), Aerodynamic Coefficient Identification (ACIP)/High Resolution Accelerom- Identification (ACIP)/High Resolution Accelerom- Identification (ACIP)/High Resolution Accelerom- eter Package (HIRAP) eter Package (HIRAP) eter Package (HIRAP)

41-C Mission Facts (STS-13) — Challenger — 41-C Mission Facts (STS-13) — Challenger — 41-C Mission Facts (STS-13) — Challenger — April 6–13, 1984 April 6–13, 1984 April 6–13, 1984

Commander: Robert Crippen Commander: Robert Crippen Commander: Robert Crippen Pilot: Francis (Dick) Scobee Pilot: Francis (Dick) Scobee Pilot: Francis (Dick) Scobee Mission Specialist: Terry Hart Mission Specialist: Terry Hart Mission Specialist: Terry Hart Mission Specialist: James van Hoften Mission Specialist: James van Hoften Mission Specialist: James van Hoften Mission Specialist: George Nelson Mission Specialist: George Nelson Mission Specialist: George Nelson Mission Duration: 144 hours (6 days), 23 hours, 40 Mission Duration: 144 hours (6 days), 23 hours, 40 Mission Duration: 144 hours (6 days), 23 hours, 40 minutes, 7 seconds minutes, 7 seconds minutes, 7 seconds Miles Traveled: 2.87 million statute miles Miles Traveled: 2.87 million statute miles Miles Traveled: 2.87 million statute miles Inclination: 28.45 degrees Inclination: 28.45 degrees Inclination: 28.45 degrees Orbits of Earth: 107 Orbits of Earth: 107 Orbits of Earth: 107 Orbital Altitude: Averaged out as approximately 272 Orbital Altitude: Averaged out as approximately 272 Orbital Altitude: Averaged out as approximately 272 nautical miles (313 statute miles) circular orbit nautical miles (313 statute miles) circular orbit nautical miles (313 statute miles) circular orbit Extravehicular Activity (EVA): James van Hoften and Extravehicular Activity (EVA): James van Hoften and Extravehicular Activity (EVA): James van Hoften and George Nelson. EVA No. 1 duration 2 hours, George Nelson. EVA No. 1 duration 2 hours, George Nelson. EVA No. 1 duration 2 hours, 59 minutes, EVA No. 2 duration 7 hours, 7 minutes. 59 minutes, EVA No. 2 duration 7 hours, 7 minutes. 59 minutes, EVA No. 2 duration 7 hours, 7 minutes. Manned maneuvering unit (MMU) operating time, Manned maneuvering unit (MMU) operating time, Manned maneuvering unit (MMU) operating time, George Nelson 42 minutes, James van Hoften George Nelson 42 minutes, James van Hoften George Nelson 42 minutes, James van Hoften 28 minutes 28 minutes 28 minutes Landing Touchdown: Approximately 1,912 feet beyond Landing Touchdown: Approximately 1,912 feet beyond Landing Touchdown: Approximately 1,912 feet beyond planned touchdown threshold point planned touchdown threshold point planned touchdown threshold point Landing Rollout: Approximately 8,716 feet from main Landing Rollout: Approximately 8,716 feet from main Landing Rollout: Approximately 8,716 feet from main gear touchdown gear touchdown gear touchdown Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately 196,975 pounds 196,975 pounds 196,975 pounds Lift-off Weight: Approximately 4,508,234 pounds Lift-off Weight: Approximately 4,508,234 pounds Lift-off Weight: Approximately 4,508,234 pounds Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately 254,329 pounds 254,329 pounds 254,329 pounds

Y-8 Y-8 Y-8 41-C Mission Facts (Cont) 41-C Mission Facts (Cont) 41-C Mission Facts (Cont)

Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 213 knots (245 miles per hour) mately 213 knots (245 miles per hour) mately 213 knots (245 miles per hour) Cargo Weight Up: Approximately 38,266 pounds Cargo Weight Up: Approximately 38,266 pounds Cargo Weight Up: Approximately 38,266 pounds Cargo Weight Down: Approximately 16,870 pounds Cargo Weight Down: Approximately 16,870 pounds Cargo Weight Down: Approximately 16,870 pounds Landed: Runway 17 dry lake bed at Edwards Air Force Landed: Runway 17 dry lake bed at Edwards Air Force Landed: Runway 17 dry lake bed at Edwards Air Force Base, California Base, California Base, California First repair on orbit of a satellite, Solar Maximum Mis- First repair on orbit of a satellite, Solar Maximum Mis- First repair on orbit of a satellite, Solar Maximum Mis- sion, by James van Hoften and George Nelson sion, by James van Hoften and George Nelson sion, by James van Hoften and George Nelson Payloads: Solar Maximum Mission (SMM) repair, Payloads: Solar Maximum Mission (SMM) repair, Payloads: Solar Maximum Mission (SMM) repair, manned maneuvering unit (MMU) satellite support, manned maneuvering unit (MMU) satellite support, manned maneuvering unit (MMU) satellite support, deployment of Long-Duration Exposure Facility deployment of Long-Duration Exposure Facility deployment of Long-Duration Exposure Facility (LDEF) in earth orbit free drift. LDEF contained 57 (LDEF) in earth orbit free drift. LDEF contained 57 (LDEF) in earth orbit free drift. LDEF contained 57 experiments and weighed about 22,000 pounds. experiments and weighed about 22,000 pounds. experiments and weighed about 22,000 pounds. Cinema 360 and IMAX 70-mm cameras. Cinema 360 and IMAX 70-mm cameras. Cinema 360 and IMAX 70-mm cameras.

41-D Mission Facts (STS-14) — Discovery — 41-D Mission Facts (STS-14) — Discovery — 41-D Mission Facts (STS-14) — Discovery — August 30–September 5, 1984 August 30–September 5, 1984 August 30–September 5, 1984

Commander: Henry Hartsfield, Jr. Commander: Henry Hartsfield, Jr. Commander: Henry Hartsfield, Jr. Pilot: Michael Coats Pilot: Michael Coats Pilot: Michael Coats Mission Specialist: Richard Mullane Mission Specialist: Richard Mullane Mission Specialist: Richard Mullane Mission Specialist: Steven Hawley Mission Specialist: Steven Hawley Mission Specialist: Steven Hawley Mission Specialist: Judith Resnik Mission Specialist: Judith Resnik Mission Specialist: Judith Resnik Payload Specialist: Charles Walker Payload Specialist: Charles Walker Payload Specialist: Charles Walker Mission Duration: 144 hours (6 days), 56 minutes, Mission Duration: 144 hours (6 days), 56 minutes, Mission Duration: 144 hours (6 days), 56 minutes, 4 seconds 4 seconds 4 seconds Miles Traveled: 2.49 million statute miles Miles Traveled: 2.49 million statute miles Miles Traveled: 2.49 million statute miles Inclination: 28.45 degrees Inclination: 28.45 degrees Inclination: 28.45 degrees Orbits of Earth: 96 Orbits of Earth: 96 Orbits of Earth: 96 Orbital Altitude: 160 by 160 nautical miles (184 by Orbital Altitude: 160 by 160 nautical miles (184 by Orbital Altitude: 160 by 160 nautical miles (184 by 184 statute miles), then 160 by 165 nautical miles 184 statute miles), then 160 by 165 nautical miles 184 statute miles), then 160 by 165 nautical miles (184 by189 statute miles), then 160 by 173 nautical (184 by189 statute miles), then 160 by 173 nautical (184 by189 statute miles), then 160 by 173 nautical miles (184 by 199 statute miles), then to 160 by miles (184 by 199 statute miles), then to 160 by miles (184 by 199 statute miles), then to 160 by 179 nautical miles (184 by 205 statute miles), then 179 nautical miles (184 by 205 statute miles), then 179 nautical miles (184 by 205 statute miles), then to 159 by 160 nautical miles (182 by 184 statute to 159 by 160 nautical miles (182 by 184 statute to 159 by 160 nautical miles (182 by 184 statute miles) miles) miles) Landing Touchdown: Approximately 2,510 feet beyond Landing Touchdown: Approximately 2,510 feet beyond Landing Touchdown: Approximately 2,510 feet beyond touchdown threshold point touchdown threshold point touchdown threshold point Landing Rollout: Approximately 10,275 feet from main Landing Rollout: Approximately 10,275 feet from main Landing Rollout: Approximately 10,275 feet from main gear touchdown gear touchdown gear touchdown Orbiter Weight at Landing: Approximately 201,674 Orbiter Weight at Landing: Approximately 201,674 Orbiter Weight at Landing: Approximately 201,674 pounds pounds pounds Lift-off Weight: Approximately 4,517,534 pounds Lift-off Weight: Approximately 4,517,534 pounds Lift-off Weight: Approximately 4,517,534 pounds Orbiter Weight at Lift-off: Approximately 263,477 Orbiter Weight at Lift-off: Approximately 263,477 Orbiter Weight at Lift-off: Approximately 263,477 pounds pounds pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 200 knots (230 miles per hour) mately 200 knots (230 miles per hour) mately 200 knots (230 miles per hour) Cargo Weight Up: Approximately 47,516 pounds Cargo Weight Up: Approximately 47,516 pounds Cargo Weight Up: Approximately 47,516 pounds Cargo Weight Down: Approximately 11,296 pounds Cargo Weight Down: Approximately 11,296 pounds Cargo Weight Down: Approximately 11,296 pounds Landed: Runway 17 dry lake bed at Edwards Air Force Landed: Runway 17 dry lake bed at Edwards Air Force Landed: Runway 17 dry lake bed at Edwards Air Force Base, California Base, California Base, California

Y-9 Y-9 Y-9 41-D Mission Facts (Cont) 41-D Mission Facts (Cont) 41-D Mission Facts (Cont)

Payloads: Satellite Business System (SBS)-D com- Payloads: Satellite Business System (SBS)-D com- Payloads: Satellite Business System (SBS)-D com- munications satellite with Payload Assist Module munications satellite with Payload Assist Module munications satellite with Payload Assist Module (PAM)-D deployment, Syncom IV-2 communica- (PAM)-D deployment, Syncom IV-2 communica- (PAM)-D deployment, Syncom IV-2 communica- tions satellite with its unique stage deployment, tions satellite with its unique stage deployment, tions satellite with its unique stage deployment, Telstar (American Telephone and Telegraph) 3-C Telstar (American Telephone and Telegraph) 3-C Telstar (American Telephone and Telegraph) 3-C with PAM-D deployment, Office of Aeronautics with PAM-D deployment, Office of Aeronautics with PAM-D deployment, Office of Aeronautics and Space Technology (OAST)-1 experiments. and Space Technology (OAST)-1 experiments. and Space Technology (OAST)-1 experiments. Deployment and restowing of large solar array. Deployment and restowing of large solar array. Deployment and restowing of large solar array. Continuous Flow Electrophoresis (CFES). IMAX Continuous Flow Electrophoresis (CFES). IMAX Continuous Flow Electrophoresis (CFES). IMAX camera camera camera A student experiment, sponsored by Rockwell In- A student experiment, sponsored by Rockwell In- A student experiment, sponsored by Rockwell In- ternational, of indium crystal growth using the float ternational, of indium crystal growth using the float ternational, of indium crystal growth using the float zone technique was successful, although a blown zone technique was successful, although a blown zone technique was successful, although a blown fuse resulted in a premature shutdown. fuse resulted in a premature shutdown. fuse resulted in a premature shutdown.

41-G Mission Facts (STS-17) — Challenger — 41-G Mission Facts (STS-17) — Challenger — 41-G Mission Facts (STS-17) — Challenger — October 5–13, 1984 October 5–13, 1984 October 5–13, 1984

Commander: Robert Crippen Commander: Robert Crippen Commander: Robert Crippen Pilot: Jon McBride Pilot: Jon McBride Pilot: Jon McBride Mission Specialist: David Leestma Mission Specialist: David Leestma Mission Specialist: David Leestma Mission Specialist: Sally Ride Mission Specialist: Sally Ride Mission Specialist: Sally Ride Mission Specialist: Kathryn Sullivan Mission Specialist: Kathryn Sullivan Mission Specialist: Kathryn Sullivan Payload Specialist: Paul Scully-Power Payload Specialist: Paul Scully-Power Payload Specialist: Paul Scully-Power Payload Specialist: Marc Garneau Payload Specialist: Marc Garneau Payload Specialist: Marc Garneau Mission Duration: 192 hours (8 days), 5 hours, Mission Duration: 192 hours (8 days), 5 hours, Mission Duration: 192 hours (8 days), 5 hours, 23 minutes, 33 seconds 23 minutes, 33 seconds 23 minutes, 33 seconds Miles Traveled: 3,434,444 statute miles Miles Traveled: 3,434,444 statute miles Miles Traveled: 3,434,444 statute miles Inclination: 57 degrees Inclination: 57 degrees Inclination: 57 degrees Orbits of Earth: 132 Orbits of Earth: 132 Orbits of Earth: 132 Orbital Altitude: 190 by 190 nautical miles (218 by Orbital Altitude: 190 by 190 nautical miles (218 by Orbital Altitude: 190 by 190 nautical miles (218 by 218 statute miles), then to 148 by 148 nautical 218 statute miles), then to 148 by 148 nautical 218 statute miles), then to 148 by 148 nautical miles (170 by 170 statute miles), then to 120 by miles (170 by 170 statute miles), then to 120 by miles (170 by 170 statute miles), then to 120 by 120 nautical miles (138 by 138 statute miles) 120 nautical miles (138 by 138 statute miles) 120 nautical miles (138 by 138 statute miles) Extravehicular Activity (EVA): Kathryn Sullivan and Extravehicular Activity (EVA): Kathryn Sullivan and Extravehicular Activity (EVA): Kathryn Sullivan and David Leestma. EVA duration 3 hours, 29 minutes David Leestma. EVA duration 3 hours, 29 minutes David Leestma. EVA duration 3 hours, 29 minutes Landing Touchdown: Approximately 959 feet beyond Landing Touchdown: Approximately 959 feet beyond Landing Touchdown: Approximately 959 feet beyond threshold point threshold point threshold point Landing Rollout: Approximately 10,633 feet from main Landing Rollout: Approximately 10,633 feet from main Landing Rollout: Approximately 10,633 feet from main gear touchdown gear touchdown gear touchdown Orbiter Weight at Landing: Approximately 202,266 Orbiter Weight at Landing: Approximately 202,266 Orbiter Weight at Landing: Approximately 202,266 pounds pounds pounds Lift-off Weight: Approximately 4,493,317 pounds Lift-off Weight: Approximately 4,493,317 pounds Lift-off Weight: Approximately 4,493,317 pounds Orbiter Weight at Lift-off: Approximately 242,790 Orbiter Weight at Lift-off: Approximately 242,790 Orbiter Weight at Lift-off: Approximately 242,790 pounds pounds pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 208 knots (239 miles per hour) mately 208 knots (239 miles per hour) mately 208 knots (239 miles per hour) Cargo Weight Up: Approximately 23,465 pounds Cargo Weight Up: Approximately 23,465 pounds Cargo Weight Up: Approximately 23,465 pounds Cargo Weight Down: Approximately 18,516 pounds Cargo Weight Down: Approximately 18,516 pounds Cargo Weight Down: Approximately 18,516 pounds Landed: Runway 33 at Kennedy Space Center, Florida Landed: Runway 33 at Kennedy Space Center, Florida Landed: Runway 33 at Kennedy Space Center, Florida

Y-10 Y-10 Y-10 41-G Mission Facts (Cont) 41-G Mission Facts (Cont) 41-G Mission Facts (Cont)

Payloads: Earth Radiation Budget Satellite (ERBS) Payloads: Earth Radiation Budget Satellite (ERBS) Payloads: Earth Radiation Budget Satellite (ERBS) deployment, Office of Space and Terrestrial deployment, Office of Space and Terrestrial deployment, Office of Space and Terrestrial Applications (OSTA)-3 experiments, Large Applications (OSTA)-3 experiments, Large Applications (OSTA)-3 experiments, Large Format Camera (LFC) Format Camera (LFC) Format Camera (LFC) First use of Orbital Refueling System (ORS) with First use of Orbital Refueling System (ORS) with First use of Orbital Refueling System (ORS) with extravehicular activity (EVA) astronauts, IMAX extravehicular activity (EVA) astronauts, IMAX extravehicular activity (EVA) astronauts, IMAX camera camera camera

51-A Mission Facts — Discovery — 51-A Mission Facts — Discovery — 51-A Mission Facts — Discovery — November 8–16, 1984 November 8–16, 1984 November 8–16, 1984

Commander: Frederick Hauck Commander: Frederick Hauck Commander: Frederick Hauck Pilot: David Walker Pilot: David Walker Pilot: David Walker Mission Specialist: Joseph Allen Mission Specialist: Joseph Allen Mission Specialist: Joseph Allen Mission Specialist: Anna Fisher Mission Specialist: Anna Fisher Mission Specialist: Anna Fisher Mission Specialist: Dale Gardner Mission Specialist: Dale Gardner Mission Specialist: Dale Gardner Mission Duration: 168 hours (7 days), 23 hours, 44 min- Mission Duration: 168 hours (7 days), 23 hours, 44 min- Mission Duration: 168 hours (7 days), 23 hours, 44 min- utes, 56 seconds utes, 56 seconds utes, 56 seconds Miles Traveled: 3,289,406 statute miles Miles Traveled: 3,289,406 statute miles Miles Traveled: 3,289,406 statute miles Inclination: 28.5 degrees Inclination: 28.5 degrees Inclination: 28.5 degrees Orbits of Earth: 126 Orbits of Earth: 126 Orbits of Earth: 126 Orbital Altitude: 161 by 151 nautical miles (nmi) (185 by Orbital Altitude: 161 by 151 nautical miles (nmi) (185 by Orbital Altitude: 161 by 151 nautical miles (nmi) (185 by 173 statute miles [sm]), then 161 by 156 nmi (185 173 statute miles [sm]), then 161 by 156 nmi (185 173 statute miles [sm]), then 161 by 156 nmi (185 by 179 sm), then to 163 by 156 nmi (187 by 179 by 179 sm), then to 163 by 156 nmi (187 by 179 by 179 sm), then to 163 by 156 nmi (187 by 179 sm), then to163 by 163 nmi (187 by 187 sm), then sm), then to163 by 163 nmi (187 by 187 sm), then sm), then to163 by 163 nmi (187 by 187 sm), then to169 by163 nmi (194 by 187 sm), then to 171 by to169 by163 nmi (194 by 187 sm), then to 171 by to169 by163 nmi (194 by 187 sm), then to 171 by 169 nmi (196 by 194 sm), then to 174 by 169 nmi 169 nmi (196 by 194 sm), then to 174 by 169 nmi 169 nmi (196 by 194 sm), then to 174 by 169 nmi (200 by 194 sm), then to 178 by 174 nmi (204 by (200 by 194 sm), then to 178 by 174 nmi (204 by (200 by 194 sm), then to 178 by 174 nmi (204 by 200 sm), then to 178 by 176 nmi (204 by 202 sm), 200 sm), then to 178 by 176 nmi (204 by 202 sm), 200 sm), then to 178 by 176 nmi (204 by 202 sm), then to 193 by 176 nmi (222 by 202 sm), then to then to 193 by 176 nmi (222 by 202 sm), then to then to 193 by 176 nmi (222 by 202 sm), then to 193 by 183 nmi (222 by 210 sm), then to 195 by 193 by 183 nmi (222 by 210 sm), then to 195 by 193 by 183 nmi (222 by 210 sm), then to 195 by 189 nmi (224 by 217 sm), then to 195 by 191 nmi 189 nmi (224 by 217 sm), then to 195 by 191 nmi 189 nmi (224 by 217 sm), then to 195 by 191 nmi (224 by 219 sm), then to 193 by 183 nmi (222 by (224 by 219 sm), then to 193 by 183 nmi (222 by (224 by 219 sm), then to 193 by 183 nmi (222 by 210 sm), then to 193 by 189 nmi (222 by 217 sm), 210 sm), then to 193 by 189 nmi (222 by 217 sm), 210 sm), then to 193 by 189 nmi (222 by 217 sm), then to 195 by 190 nmi (224 by 218 sm) then to 195 by 190 nmi (224 by 218 sm) then to 195 by 190 nmi (224 by 218 sm) Landing Touchdown: Approximately 2,718 feet beyond Landing Touchdown: Approximately 2,718 feet beyond Landing Touchdown: Approximately 2,718 feet beyond threshold point threshold point threshold point Landing Rollout: Approximately 9,461 feet from main Landing Rollout: Approximately 9,461 feet from main Landing Rollout: Approximately 9,461 feet from main gear touchdown gear touchdown gear touchdown Orbiter Weight at Landing: Approximately 207,505 Orbiter Weight at Landing: Approximately 207,505 Orbiter Weight at Landing: Approximately 207,505 pounds pounds pounds Lift-off Weight: Approximately 4,519,901 pounds Lift-off Weight: Approximately 4,519,901 pounds Lift-off Weight: Approximately 4,519,901 pounds Orbiter Weight at Lift-off: Approximately 263,324 Orbiter Weight at Lift-off: Approximately 263,324 Orbiter Weight at Lift-off: Approximately 263,324 pounds pounds pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 186 knots (214 miles per hour) mately 186 knots (214 miles per hour) mately 186 knots (214 miles per hour) Cargo Weight Up: Approximately 45,306 pounds Cargo Weight Up: Approximately 45,306 pounds Cargo Weight Up: Approximately 45,306 pounds Cargo Weight Down: Approximately 24,853 pounds Cargo Weight Down: Approximately 24,853 pounds Cargo Weight Down: Approximately 24,853 pounds Landed: Runway 15 at Kennedy Space Center, Florida Landed: Runway 15 at Kennedy Space Center, Florida Landed: Runway 15 at Kennedy Space Center, Florida First retrieval of two satellites (PALAPA B-2 and First retrieval of two satellites (PALAPA B-2 and First retrieval of two satellites (PALAPA B-2 and WESTAR Vl) for return to earth. WESTAR Vl) for return to earth. WESTAR Vl) for return to earth.

Y-11 Y-11 Y-11 51-A Mission Facts (Cont) 51-A Mission Facts (Cont) 51-A Mission Facts (Cont)

Extravehicular Activity (EVA): Joseph Allen and Dale Extravehicular Activity (EVA): Joseph Allen and Dale Extravehicular Activity (EVA): Joseph Allen and Dale Gardner. EVA No. 1 duration, 6 hours, 13 minutes. Gardner. EVA No. 1 duration, 6 hours, 13 minutes. Gardner. EVA No. 1 duration, 6 hours, 13 minutes. EVA No. 2 duration, 6 hours and 1 minute. Manned EVA No. 2 duration, 6 hours and 1 minute. Manned EVA No. 2 duration, 6 hours and 1 minute. Manned maneuvering unit (MMU) operating time Joseph maneuvering unit (MMU) operating time Joseph maneuvering unit (MMU) operating time Joseph Allen 2 hours, 22 minutes, Dale Gardner 1 hour, Allen 2 hours, 22 minutes, Dale Gardner 1 hour, Allen 2 hours, 22 minutes, Dale Gardner 1 hour, 40 minutes 40 minutes 40 minutes Payloads: Telesat (Canada communications satellite)-H Payloads: Telesat (Canada communications satellite)-H Payloads: Telesat (Canada communications satellite)-H with Payload Assist Module (PAM)-D deployment, with Payload Assist Module (PAM)-D deployment, with Payload Assist Module (PAM)-D deployment, Syncom IV-1 communications satellite deploy- Syncom IV-1 communications satellite deploy- Syncom IV-1 communications satellite deploy- ment with its unique stage, retrieval of PALAPA ment with its unique stage, retrieval of PALAPA ment with its unique stage, retrieval of PALAPA B-2 and WESTAR VI communications satellites B-2 and WESTAR VI communications satellites B-2 and WESTAR VI communications satellites with PAM-D which failed to ignite on the STS-41-B with PAM-D which failed to ignite on the STS-41-B with PAM-D which failed to ignite on the STS-41-B mission. Manned maneuvering unit (MMU) used mission. Manned maneuvering unit (MMU) used mission. Manned maneuvering unit (MMU) used for retrieval. for retrieval. for retrieval. Diffusive Mixing of Organic Solutions (DMOS) Diffusive Mixing of Organic Solutions (DMOS) Diffusive Mixing of Organic Solutions (DMOS) experiment experiment experiment

51-C Mission Facts — Discovery — 51-C Mission Facts — Discovery — 51-C Mission Facts — Discovery — January 24–27, 1985 January 24–27, 1985 January 24–27, 1985

Commander: Thomas K. Mattingly Il Commander: Thomas K. Mattingly Il Commander: Thomas K. Mattingly Il Pilot: Loren J. Shriver Pilot: Loren J. Shriver Pilot: Loren J. Shriver Mission Specialist: Ellison S. Onizuka Mission Specialist: Ellison S. Onizuka Mission Specialist: Ellison S. Onizuka Mission Specialist: James F. Buchli Mission Specialist: James F. Buchli Mission Specialist: James F. Buchli Payload Specialist: Gary E. Payton Payload Specialist: Gary E. Payton Payload Specialist: Gary E. Payton Mission Duration: 72 hours (3 days), 1 hour, Mission Duration: 72 hours (3 days), 1 hour, Mission Duration: 72 hours (3 days), 1 hour, 33 minutes, 23 seconds 33 minutes, 23 seconds 33 minutes, 23 seconds Inclination: 28.45 degrees Inclination: 28.45 degrees Inclination: 28.45 degrees Orbits of Earth: 48 Orbits of Earth: 48 Orbits of Earth: 48 Landing Touchdown: Approximately 2,753 feet beyond Landing Touchdown: Approximately 2,753 feet beyond Landing Touchdown: Approximately 2,753 feet beyond runway threshold runway threshold runway threshold Landing Rollout: Approximately 7,352 feet Landing Rollout: Approximately 7,352 feet Landing Rollout: Approximately 7,352 feet Landing Speed at Main Gear Touchdown: Landing Speed at Main Gear Touchdown: Landing Speed at Main Gear Touchdown: Approximately 185 knots (212 miles per hour) Approximately 185 knots (212 miles per hour) Approximately 185 knots (212 miles per hour) Landed: Runway 15 at Kennedy Space Center, Landed: Runway 15 at Kennedy Space Center, Landed: Runway 15 at Kennedy Space Center, Florida Florida Florida Payload: DOD Payload: DOD Payload: DOD

51-D Mission Facts — Discovery — 51-D Mission Facts — Discovery — 51-D Mission Facts — Discovery — April 12–19, 1985 April 12–19, 1985 April 12–19, 1985

Commander: Karol J. Bobko Commander: Karol J. Bobko Commander: Karol J. Bobko Pilot: Donald E. Williams Pilot: Donald E. Williams Pilot: Donald E. Williams Mission Specialist: Jeffrey A. Hoffman Mission Specialist: Jeffrey A. Hoffman Mission Specialist: Jeffrey A. Hoffman Mission Specialist: S. David Griggs Mission Specialist: S. David Griggs Mission Specialist: S. David Griggs Mission Specialist: Margaret Rhea Seddon Mission Specialist: Margaret Rhea Seddon Mission Specialist: Margaret Rhea Seddon Payload Specialist: Charles D. Walker Payload Specialist: Charles D. Walker Payload Specialist: Charles D. Walker Payload Specialist: Senator Jake Garn (Utah) Payload Specialist: Senator Jake Garn (Utah) Payload Specialist: Senator Jake Garn (Utah)

Y-12 Y-12 Y-12 51-D Mission Facts (Cont) 51-D Mission Facts (Cont) 51-D Mission Facts (Cont)

Mission Duration: 144 hours (6 days), 23 hours, Mission Duration: 144 hours (6 days), 23 hours, Mission Duration: 144 hours (6 days), 23 hours, 55 minutes, 23 seconds 55 minutes, 23 seconds 55 minutes, 23 seconds Miles Traveled: 2,889,785 statute miles Miles Traveled: 2,889,785 statute miles Miles Traveled: 2,889,785 statute miles Inclination: 28.45 degrees Inclination: 28.45 degrees Inclination: 28.45 degrees Orbits of Earth: 109 Orbits of Earth: 109 Orbits of Earth: 109 Orbital Altitude: 248 by 160 nautical miles (nmi) (285 Orbital Altitude: 248 by 160 nautical miles (nmi) (285 Orbital Altitude: 248 by 160 nautical miles (nmi) (285 by 184 statute miles [sm]), then to 249 by 161 nmi by 184 statute miles [sm]), then to 249 by 161 nmi by 184 statute miles [sm]), then to 249 by 161 nmi (286 by 185 sm), then to 249 by 167 nmi (286 by (286 by 185 sm), then to 249 by 167 nmi (286 by (286 by 185 sm), then to 249 by 167 nmi (286 by 192 sm), then to 250 by 174 nmi (287 by 200 sm), 192 sm), then to 250 by 174 nmi (287 by 200 sm), 192 sm), then to 250 by 174 nmi (287 by 200 sm), then to 250 by 167 nmi (287 by 192 sm) then to 250 by 167 nmi (287 by 192 sm) then to 250 by 167 nmi (287 by 192 sm) Landing Touchdown: Approximately 1,639 feet beyond Landing Touchdown: Approximately 1,639 feet beyond Landing Touchdown: Approximately 1,639 feet beyond runway threshold runway threshold runway threshold Landing Rollout: Approximately 10,430 feet from main Landing Rollout: Approximately 10,430 feet from main Landing Rollout: Approximately 10,430 feet from main gear touchdown gear touchdown gear touchdown Orbiter Weight at Landing: Approximately 198,014 Orbiter Weight at Landing: Approximately 198,014 Orbiter Weight at Landing: Approximately 198,014 pounds pounds pounds Lift-off Weight: Approximately 4,505,245 pounds Lift-off Weight: Approximately 4,505,245 pounds Lift-off Weight: Approximately 4,505,245 pounds Orbiter Weight at Lift-off: Approximately 250,891 Orbiter Weight at Lift-off: Approximately 250,891 Orbiter Weight at Lift-off: Approximately 250,891 pounds pounds pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 200 knots (230 miles per hour) mately 200 knots (230 miles per hour) mately 200 knots (230 miles per hour) Cargo Weight Up: Approximately 35,824 pounds Cargo Weight Up: Approximately 35,824 pounds Cargo Weight Up: Approximately 35,824 pounds Cargo Weight Down: Approximately 13,248 pounds Cargo Weight Down: Approximately 13,248 pounds Cargo Weight Down: Approximately 13,248 pounds Landed: Runway 33 at Kennedy Space Center, Florida Landed: Runway 33 at Kennedy Space Center, Florida Landed: Runway 33 at Kennedy Space Center, Florida Extravehicular activity (EVA): Jeffrey Hoffman and Extravehicular activity (EVA): Jeffrey Hoffman and Extravehicular activity (EVA): Jeffrey Hoffman and David Griggs, duration, 3 hours, 10 minutes David Griggs, duration, 3 hours, 10 minutes David Griggs, duration, 3 hours, 10 minutes Payloads: Telesat (Canada communications satellite)-I Payloads: Telesat (Canada communications satellite)-I Payloads: Telesat (Canada communications satellite)-I with Payload Assist Module (PAM)-D deployment, with Payload Assist Module (PAM)-D deployment, with Payload Assist Module (PAM)-D deployment, Syncom IV-3 communications satellite deployment Syncom IV-3 communications satellite deployment Syncom IV-3 communications satellite deployment with its unique stage (unique stage failed to ignite), with its unique stage (unique stage failed to ignite), with its unique stage (unique stage failed to ignite), Continuous Flow Electrophoresis (CFES), Phase Continuous Flow Electrophoresis (CFES), Phase Continuous Flow Electrophoresis (CFES), Phase Partitioning Experiment (PPE), student experi- Partitioning Experiment (PPE), student experi- Partitioning Experiment (PPE), student experi- ments, two getaway specials (GAS) ments, two getaway specials (GAS) ments, two getaway specials (GAS) Informal science studies (Toys in Space) Informal science studies (Toys in Space) Informal science studies (Toys in Space)

51-B Mission Facts — Challenger — 51-B Mission Facts — Challenger — 51-B Mission Facts — Challenger — April 29–May 6, 1985 April 29–May 6, 1985 April 29–May 6, 1985

Commander: Robert F. Overmyer Commander: Robert F. Overmyer Commander: Robert F. Overmyer Pilot: Frederick D. Gregory Pilot: Frederick D. Gregory Pilot: Frederick D. Gregory Mission Specialist: Don Leslie Lind Mission Specialist: Don Leslie Lind Mission Specialist: Don Leslie Lind Mission Specialist: Norman E. Thagard Mission Specialist: Norman E. Thagard Mission Specialist: Norman E. Thagard Mission Specialist: William E. Thornton Mission Specialist: William E. Thornton Mission Specialist: William E. Thornton Payload Specialist: Taylor E. Wang Payload Specialist: Taylor E. Wang Payload Specialist: Taylor E. Wang Payload Specialist: Lodewijk van den Berg Payload Specialist: Lodewijk van den Berg Payload Specialist: Lodewijk van den Berg Mission Duration: 168 hours (7 days), 8 minutes, Mission Duration: 168 hours (7 days), 8 minutes, Mission Duration: 168 hours (7 days), 8 minutes, 46 seconds 46 seconds 46 seconds Miles Traveled: Approximately 2,890,383 statute Miles Traveled: Approximately 2,890,383 statute Miles Traveled: Approximately 2,890,383 statute miles miles miles Inclination: 57 degrees Inclination: 57 degrees Inclination: 57 degrees

Y-13 Y-13 Y-13 51-B Mission Facts (Cont) 51-B Mission Facts (Cont) 51-B Mission Facts (Cont)

Orbits of Earth: 110 Orbits of Earth: 110 Orbits of Earth: 110 Orbital Altitude: 193 nautical miles (222 statute miles) Orbital Altitude: 193 nautical miles (222 statute miles) Orbital Altitude: 193 nautical miles (222 statute miles) Landing Touchdown: Approximately 1,576 feet beyond Landing Touchdown: Approximately 1,576 feet beyond Landing Touchdown: Approximately 1,576 feet beyond runway threshold runway threshold runway threshold Landing Rollout: Approximately 8,317 feet Landing Rollout: Approximately 8,317 feet Landing Rollout: Approximately 8,317 feet Orbiter Weight at Landing: Approximately 212,465 Orbiter Weight at Landing: Approximately 212,465 Orbiter Weight at Landing: Approximately 212,465 pounds pounds pounds Lift-off Weight: Approximately 4,512,009 pounds Lift-off Weight: Approximately 4,512,009 pounds Lift-off Weight: Approximately 4,512,009 pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 204 knots (234 miles per hour) mately 204 knots (234 miles per hour) mately 204 knots (234 miles per hour) Cargo Weight Up: Approximately 31,407 pounds Cargo Weight Up: Approximately 31,407 pounds Cargo Weight Up: Approximately 31,407 pounds Cargo Weight Down: Approximately 31,302 pounds Cargo Weight Down: Approximately 31,302 pounds Cargo Weight Down: Approximately 31,302 pounds Landed: Runway 17 dry lake bed at Edwards Air Force Landed: Runway 17 dry lake bed at Edwards Air Force Landed: Runway 17 dry lake bed at Edwards Air Force Base, California Base, California Base, California Payloads: Spacelab-3 experiments, habitable Spacelab Payloads: Spacelab-3 experiments, habitable Spacelab Payloads: Spacelab-3 experiments, habitable Spacelab and mission peculiar experiment support struc- and mission peculiar experiment support struc- and mission peculiar experiment support struc- ture. The experiments represented a total of five ture. The experiments represented a total of five ture. The experiments represented a total of five different disciplines: materials processing in different disciplines: materials processing in different disciplines: materials processing in space, environmental observations, life science, space, environmental observations, life science, space, environmental observations, life science, astrophysics, and technology experiments. Two astrophysics, and technology experiments. Two astrophysics, and technology experiments. Two getaway specials (GAS). getaway specials (GAS). getaway specials (GAS). The flight crew was split into gold and silver shifts The flight crew was split into gold and silver shifts The flight crew was split into gold and silver shifts working 12-hour days during the flight. working 12-hour days during the flight. working 12-hour days during the flight.

51-G Mission Facts — Discovery — 51-G Mission Facts — Discovery — 51-G Mission Facts — Discovery — June 17–24, 1985 June 17–24, 1985 June 17–24, 1985

Commander: Daniel Brandenstein Commander: Daniel Brandenstein Commander: Daniel Brandenstein Pilot: John Creighton Pilot: John Creighton Pilot: John Creighton Mission Specialist: John Fabian Mission Specialist: John Fabian Mission Specialist: John Fabian Mission Specialist: Steven Nagel Mission Specialist: Steven Nagel Mission Specialist: Steven Nagel Mission Specialist: Shannon Lucid Mission Specialist: Shannon Lucid Mission Specialist: Shannon Lucid Payload Specialist: Patrick Baudry Payload Specialist: Patrick Baudry Payload Specialist: Patrick Baudry Payload Specialist: Sultan Salman Abdul Azziz Al Sa’ud Payload Specialist: Sultan Salman Abdul Azziz Al Sa’ud Payload Specialist: Sultan Salman Abdul Azziz Al Sa’ud Mission Duration: 168 hours (7 days), 1 hour, 38 min- Mission Duration: 168 hours (7 days), 1 hour, 38 min- Mission Duration: 168 hours (7 days), 1 hour, 38 min- utes, 52 seconds utes, 52 seconds utes, 52 seconds Miles Traveled: Approximately 2,916,127 statute miles Miles Traveled: Approximately 2,916,127 statute miles Miles Traveled: Approximately 2,916,127 statute miles Inclination: 28.45 degrees Inclination: 28.45 degrees Inclination: 28.45 degrees Orbits of Earth: 111 Orbits of Earth: 111 Orbits of Earth: 111 Orbital Altitude: 190 by 191 nautical miles (nmi) (218 by Orbital Altitude: 190 by 191 nautical miles (nmi) (218 by Orbital Altitude: 190 by 191 nautical miles (nmi) (218 by 219 statute miles [sm]), then 191 by 197 nmi (219 219 statute miles [sm]), then 191 by 197 nmi (219 219 statute miles [sm]), then 191 by 197 nmi (219 by 226 sm), then 191 by 203 nmi (219 by 233 sm), by 226 sm), then 191 by 203 nmi (219 by 233 sm), by 226 sm), then 191 by 203 nmi (219 by 233 sm), then to 191 by 209 nmi (219 by 240 sm), then to then to 191 by 209 nmi (219 by 240 sm), then to then to 191 by 209 nmi (219 by 240 sm), then to 191 by 207 nmi (219 by 238 sm), then to 189 by 191 by 207 nmi (219 by 238 sm), then to 189 by 191 by 207 nmi (219 by 238 sm), then to 189 by 207 nmi (217 by 238 sm), then to 163 by 191 nmi 207 nmi (217 by 238 sm), then to 163 by 191 nmi 207 nmi (217 by 238 sm), then to 163 by 191 nmi (187 by 219 sm) (187 by 219 sm) (187 by 219 sm) Landing Touchdown: Approximately 1,117 feet beyond Landing Touchdown: Approximately 1,117 feet beyond Landing Touchdown: Approximately 1,117 feet beyond threshold threshold threshold Landing Rollout: Approximately 7,433 feet Landing Rollout: Approximately 7,433 feet Landing Rollout: Approximately 7,433 feet Orbiter Weight at Lift-off: Approximately 256,421 Orbiter Weight at Lift-off: Approximately 256,421 Orbiter Weight at Lift-off: Approximately 256,421 pounds pounds pounds

Y-14 Y-14 Y-14 51-G Mission Facts (Cont) 51-G Mission Facts (Cont) 51-G Mission Facts (Cont)

Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately 204,169 pounds 204,169 pounds 204,169 pounds Lift-off Weight: Approximately 4,516,613 pounds Lift-off Weight: Approximately 4,516,613 pounds Lift-off Weight: Approximately 4,516,613 pounds Cargo Weight Up: Approximately 44,477 pounds Cargo Weight Up: Approximately 44,477 pounds Cargo Weight Up: Approximately 44,477 pounds Cargo Weight Down: Approximately 21,645 pounds Cargo Weight Down: Approximately 21,645 pounds Cargo Weight Down: Approximately 21,645 pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 198 knots (227 miles per hour) mately 198 knots (227 miles per hour) mately 198 knots (227 miles per hour) Landed: Runway 23 dry lake bed at Edwards Air Force Landed: Runway 23 dry lake bed at Edwards Air Force Landed: Runway 23 dry lake bed at Edwards Air Force Base, California Base, California Base, California Payloads: Deployment of Morelos (Mexico communi- Payloads: Deployment of Morelos (Mexico communi- Payloads: Deployment of Morelos (Mexico communi- cations satellite)-A with Payload Assist Module cations satellite)-A with Payload Assist Module cations satellite)-A with Payload Assist Module (PAM)-D, Arabsat (Arab League communications (PAM)-D, Arabsat (Arab League communications (PAM)-D, Arabsat (Arab League communications satellite)-1B with PAM-D, and Telstar (American satellite)-1B with PAM-D, and Telstar (American satellite)-1B with PAM-D, and Telstar (American Telephone and Telegraph communications satel- Telephone and Telegraph communications satel- Telephone and Telegraph communications satel- lite) with PAM-D; Shuttle Pointed Autonomous lite) with PAM-D; Shuttle Pointed Autonomous lite) with PAM-D; Shuttle Pointed Autonomous Research Tool for Astronomy (SPARTAN)-1; Auto- Research Tool for Astronomy (SPARTAN)-1; Auto- Research Tool for Astronomy (SPARTAN)-1; Auto- mated Directional Solidification Furnace (ADSF); mated Directional Solidification Furnace (ADSF); mated Directional Solidification Furnace (ADSF); High Precision Tracking Experiment (HPTE); Or- High Precision Tracking Experiment (HPTE); Or- High Precision Tracking Experiment (HPTE); Or- biter Experiments (OEX); French Echocardiograph biter Experiments (OEX); French Echocardiograph biter Experiments (OEX); French Echocardiograph Experiment (FEE) and French Pocket Experiment Experiment (FEE) and French Pocket Experiment Experiment (FEE) and French Pocket Experiment (FPE) (FPE) (FPE)

51-F Mission Facts — Challenger — 51-F Mission Facts — Challenger — 51-F Mission Facts — Challenger — July 29–August 6, 1985 July 29–August 6, 1985 July 29–August 6, 1985

Commander: Gordon Fullerton Commander: Gordon Fullerton Commander: Gordon Fullerton Pilot: Roy Bridges Pilot: Roy Bridges Pilot: Roy Bridges Mission Specialist: Story Musgrave Mission Specialist: Story Musgrave Mission Specialist: Story Musgrave Mission Specialist: Anthony England Mission Specialist: Anthony England Mission Specialist: Anthony England Mission Specialist: Karl Henize Mission Specialist: Karl Henize Mission Specialist: Karl Henize Payload Specialist: Loren Acton Payload Specialist: Loren Acton Payload Specialist: Loren Acton Payload Specialist: John-David Bartoe Payload Specialist: John-David Bartoe Payload Specialist: John-David Bartoe Mission Duration: 168 hours (7 days), 22 hours, Mission Duration: 168 hours (7 days), 22 hours, Mission Duration: 168 hours (7 days), 22 hours, 45 minutes, 26 seconds 45 minutes, 26 seconds 45 minutes, 26 seconds Miles Traveled: Approximately 3,283,543 statute miles Miles Traveled: Approximately 3,283,543 statute miles Miles Traveled: Approximately 3,283,543 statute miles Inclination: 49.5 degrees Inclination: 49.5 degrees Inclination: 49.5 degrees Orbits of Earth: 126 Orbits of Earth: 126 Orbits of Earth: 126 Orbital Altitude: 143 by 108 nautical miles (nmi) (164 Orbital Altitude: 143 by 108 nautical miles (nmi) (164 Orbital Altitude: 143 by 108 nautical miles (nmi) (164 by 124 statute miles [sm]), 169 by 170 nmi (194 by by 124 statute miles [sm]), 169 by 170 nmi (194 by by 124 statute miles [sm]), 169 by 170 nmi (194 by 195 sm), 168 by 170 nmi (193 by 195 sm), 170 by 195 sm), 168 by 170 nmi (193 by 195 sm), 170 by 195 sm), 168 by 170 nmi (193 by 195 sm), 170 by 172 nmi (195 by 197 sm), 170 by 171 nmi (195 by 172 nmi (195 by 197 sm), 170 by 171 nmi (195 by 172 nmi (195 by 197 sm), 170 by 171 nmi (195 by 196 sm), 166 by 173 nmi (191 by 199 sm), 167 by 196 sm), 166 by 173 nmi (191 by 199 sm), 167 by 196 sm), 166 by 173 nmi (191 by 199 sm), 167 by 171 nmi (192 by 196 sm), 165 by 174 nmi (189 by 171 nmi (192 by 196 sm), 165 by 174 nmi (189 by 171 nmi (192 by 196 sm), 165 by 174 nmi (189 by 200 sm) 200 sm) 200 sm) Landing Touchdown: Approximately 3,713 feet beyond Landing Touchdown: Approximately 3,713 feet beyond Landing Touchdown: Approximately 3,713 feet beyond threshold threshold threshold Landing Rollout: Approximately 8,569 feet Landing Rollout: Approximately 8,569 feet Landing Rollout: Approximately 8,569 feet Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately 252,628 pounds 252,628 pounds 252,628 pounds Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately 216,735 pounds 216,735 pounds 216,735 pounds Lift-off Weight: Approximately 4,515,554 pounds Lift-off Weight: Approximately 4,515,554 pounds Lift-off Weight: Approximately 4,515,554 pounds

Y-15 Y-15 Y-15 51-F Mission Facts (Cont) 51-F Mission Facts (Cont) 51-F Mission Facts (Cont) Cargo Weight Up and Down: Approximately Cargo Weight Up and Down: Approximately Cargo Weight Up and Down: Approximately 34,400 pounds 34,400 pounds 34,400 pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 199 knots (229 miles per hour) mately 199 knots (229 miles per hour) mately 199 knots (229 miles per hour) Landed: Runway 23 dry lake bed at Edwards Air Force Landed: Runway 23 dry lake bed at Edwards Air Force Landed: Runway 23 dry lake bed at Edwards Air Force Base, California Base, California Base, California Payloads: Spacelab-2 with 13 experiments, Shuttle Payloads: Spacelab-2 with 13 experiments, Shuttle Payloads: Spacelab-2 with 13 experiments, Shuttle Amateur Radio Experiment (SAREX), Protein Crys- Amateur Radio Experiment (SAREX), Protein Crys- Amateur Radio Experiment (SAREX), Protein Crys- tal Growth (PCG). The flight crew was divided into tal Growth (PCG). The flight crew was divided into tal Growth (PCG). The flight crew was divided into a red and blue team. Each team worked 12-hour a red and blue team. Each team worked 12-hour a red and blue team. Each team worked 12-hour shifts for 24-hour-a-day operation. shifts for 24-hour-a-day operation. shifts for 24-hour-a-day operation. At 5 minutes, 45 seconds into ascent the number one At 5 minutes, 45 seconds into ascent the number one At 5 minutes, 45 seconds into ascent the number one engine shut down prematurely and an abort to engine shut down prematurely and an abort to engine shut down prematurely and an abort to orbit was declared. orbit was declared. orbit was declared.

51-I Mission Facts — Discovery — 51-I Mission Facts — Discovery — 51-I Mission Facts — Discovery — August 27–September 3, 1985 August 27–September 3, 1985 August 27–September 3, 1985

Commander: Joe H. Engle Commander: Joe H. Engle Commander: Joe H. Engle Pilot: Richard O. Covey Pilot: Richard O. Covey Pilot: Richard O. Covey Mission Specialist: James van Hoften Mission Specialist: James van Hoften Mission Specialist: James van Hoften Mission Specialist: William F. Fisher Mission Specialist: William F. Fisher Mission Specialist: William F. Fisher Mission Specialist: John M. Lounge Mission Specialist: John M. Lounge Mission Specialist: John M. Lounge Mission Duration: 168 hours (7 days), 2 hours, Mission Duration: 168 hours (7 days), 2 hours, Mission Duration: 168 hours (7 days), 2 hours, 17 minutes, 42 seconds 17 minutes, 42 seconds 17 minutes, 42 seconds Miles Traveled: 2,919,576 statute miles Miles Traveled: 2,919,576 statute miles Miles Traveled: 2,919,576 statute miles Inclination: 28.45 degrees Inclination: 28.45 degrees Inclination: 28.45 degrees Orbits of Earth: 111 Orbits of Earth: 111 Orbits of Earth: 111 Orbital Altitude: 190 by 190 nautical miles (nmi) (218 Orbital Altitude: 190 by 190 nautical miles (nmi) (218 Orbital Altitude: 190 by 190 nautical miles (nmi) (218 by 218 statute miles [sm]), 196 by 191 nmi (225 by by 218 statute miles [sm]), 196 by 191 nmi (225 by by 218 statute miles [sm]), 196 by 191 nmi (225 by 219 sm), 202 by 190 nmi (232 by 218 sm), 202 by 219 sm), 202 by 190 nmi (232 by 218 sm), 202 by 219 sm), 202 by 190 nmi (232 by 218 sm), 202 by 191 nmi (232 by 219 sm), 212 by 170 nmi (243 by 191 nmi (232 by 219 sm), 212 by 170 nmi (243 by 191 nmi (232 by 219 sm), 212 by 170 nmi (243 by 195 sm), 239 by 169 nmi (275 by 194 sm), 242 by 195 sm), 239 by 169 nmi (275 by 194 sm), 242 by 195 sm), 239 by 169 nmi (275 by 194 sm), 242 by 169 nmi (278 by 194 sm), 242 by 178 nmi (278 by 169 nmi (278 by 194 sm), 242 by 178 nmi (278 by 169 nmi (278 by 194 sm), 242 by 178 nmi (278 by 204 sm) 204 sm) 204 sm) Landing Touchdown: Approximately 2,101 feet beyond Landing Touchdown: Approximately 2,101 feet beyond Landing Touchdown: Approximately 2,101 feet beyond threshold threshold threshold Landing Rollout: Approximately 6,100 feet Landing Rollout: Approximately 6,100 feet Landing Rollout: Approximately 6,100 feet Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately 196,674 pounds 196,674 pounds 196,674 pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 191 knots (219 miles per hour) mately 191 knots (219 miles per hour) mately 191 knots (219 miles per hour) Lift-off Weight: Approximately 4,512,130 pounds Lift-off Weight: Approximately 4,512,130 pounds Lift-off Weight: Approximately 4,512,130 pounds Orbiter Weight at Lift-off: Approximately 262,309 Orbiter Weight at Lift-off: Approximately 262,309 Orbiter Weight at Lift-off: Approximately 262,309 pounds pounds pounds Landed: Runway 23 dry lake bed at Edwards Air Force Landed: Runway 23 dry lake bed at Edwards Air Force Landed: Runway 23 dry lake bed at Edwards Air Force Base, California Base, California Base, California Extravehicular Activity (EVA): James van Hoften and Extravehicular Activity (EVA): James van Hoften and Extravehicular Activity (EVA): James van Hoften and William Fisher. EVA 1 duration approximately 7 William Fisher. EVA 1 duration approximately 7 William Fisher. EVA 1 duration approximately 7 hours, 20 minutes, EVA 2 duration approximately hours, 20 minutes, EVA 2 duration approximately hours, 20 minutes, EVA 2 duration approximately 4 hours, 31 minutes 4 hours, 31 minutes 4 hours, 31 minutes Cargo Weight Up: Approximately 43,988 pounds Cargo Weight Up: Approximately 43,988 pounds Cargo Weight Up: Approximately 43,988 pounds

Y-16 Y-16 Y-16 51-I Mission Facts (Cont) 51-I Mission Facts (Cont) 51-I Mission Facts (Cont)

Cargo Weight Down: Approximately 13,452 pounds Cargo Weight Down: Approximately 13,452 pounds Cargo Weight Down: Approximately 13,452 pounds Payloads: Deploy ASC (American Satellite Company)-1 Payloads: Deploy ASC (American Satellite Company)-1 Payloads: Deploy ASC (American Satellite Company)-1 with Payload Assist Modue (PAM)-D. with Payload Assist Modue (PAM)-D. with Payload Assist Modue (PAM)-D. Deploy AUSSAT (Australian communications satel- Deploy AUSSAT (Australian communications satel- Deploy AUSSAT (Australian communications satel- lite)-1 with PAM-D. Deploy Syncom IV-4 lite)-1 with PAM-D. Deploy Syncom IV-4 lite)-1 with PAM-D. Deploy Syncom IV-4 communications satellite with its unique stage. communications satellite with its unique stage. communications satellite with its unique stage. Retrieve Leasat-3 communications satellite, repair Retrieve Leasat-3 communications satellite, repair Retrieve Leasat-3 communications satellite, repair and deploy by extravehicular activity (EVA) astro- and deploy by extravehicular activity (EVA) astro- and deploy by extravehicular activity (EVA) astro- nauts. Physical Vapor Transport Organic Solids nauts. Physical Vapor Transport Organic Solids nauts. Physical Vapor Transport Organic Solids (PVTOS) experiment (PVTOS) experiment (PVTOS) experiment

51-J Mission Facts — Atlantis — 51-J Mission Facts — Atlantis — 51-J Mission Facts — Atlantis — October 3–7, 1985 October 3–7, 1985 October 3–7, 1985

Commander: Karol J. Bobko Commander: Karol J. Bobko Commander: Karol J. Bobko Pilot: Ronald J. Grabe Pilot: Ronald J. Grabe Pilot: Ronald J. Grabe Mission Specialist: David C. Hilmers Mission Specialist: David C. Hilmers Mission Specialist: David C. Hilmers Mission Specialist: Robert L. Stewart Mission Specialist: Robert L. Stewart Mission Specialist: Robert L. Stewart Payload Specialist: Major William A. Pailes Payload Specialist: Major William A. Pailes Payload Specialist: Major William A. Pailes Mission Duration: 96 hours (4 days), 1 hour, Mission Duration: 96 hours (4 days), 1 hour, Mission Duration: 96 hours (4 days), 1 hour, 44 minutes, 38 seconds 44 minutes, 38 seconds 44 minutes, 38 seconds Inclination: 28.5 degrees Inclination: 28.5 degrees Inclination: 28.5 degrees Orbital Altitude: 278 nautical miles (319 statute Orbital Altitude: 278 nautical miles (319 statute Orbital Altitude: 278 nautical miles (319 statute miles)* miles)* miles)* Orbits of Earth: 63 Orbits of Earth: 63 Orbits of Earth: 63 Landing Touchdown: Approximately 2,476 feet beyond Landing Touchdown: Approximately 2,476 feet beyond Landing Touchdown: Approximately 2,476 feet beyond threshold threshold threshold Landing Rollout: Approximately 8,056 feet Landing Rollout: Approximately 8,056 feet Landing Rollout: Approximately 8,056 feet Landed: Runway 23 dry lake bed at Edwards Air Force Landed: Runway 23 dry lake bed at Edwards Air Force Landed: Runway 23 dry lake bed at Edwards Air Force Base, California Base, California Base, California Payload: DOD Payload: DOD Payload: DOD *Record altitude (as of 5/93) *Record altitude (as of 5/93) *Record altitude (as of 5/93)

61-A Mission Facts — Challenger — 61-A Mission Facts — Challenger — 61-A Mission Facts — Challenger — October 30–November 6, 1985 October 30–November 6, 1985 October 30–November 6, 1985

Commander: Henry W. Hartsfield, Jr. Commander: Henry W. Hartsfield, Jr. Commander: Henry W. Hartsfield, Jr. Pilot: Steven R. Nagel Pilot: Steven R. Nagel Pilot: Steven R. Nagel Mission Specialist: James F. Buchli Mission Specialist: James F. Buchli Mission Specialist: James F. Buchli Mission Specialist: Guion S. Bluford, Jr. Mission Specialist: Guion S. Bluford, Jr. Mission Specialist: Guion S. Bluford, Jr. Mission Specialist: Bonnie J. Dunbar Mission Specialist: Bonnie J. Dunbar Mission Specialist: Bonnie J. Dunbar Payload Specialist: Reinhard Furrer, West Germany Payload Specialist: Reinhard Furrer, West Germany Payload Specialist: Reinhard Furrer, West Germany Payload Specialist: Wubbo Ockels, Netherlands Payload Specialist: Wubbo Ockels, Netherlands Payload Specialist: Wubbo Ockels, Netherlands Payload Specialist: Ernst Messerschmid, Payload Specialist: Ernst Messerschmid, Payload Specialist: Ernst Messerschmid, West Germany West Germany West Germany Mission Duration: 168 hours (7 days), 44 minutes, Mission Duration: 168 hours (7 days), 44 minutes, Mission Duration: 168 hours (7 days), 44 minutes, 51 seconds 51 seconds 51 seconds Miles Traveled: Approximately 2,909,352 Miles Traveled: Approximately 2,909,352 Miles Traveled: Approximately 2,909,352 statute miles statute miles statute miles Inclination: 57 degrees Inclination: 57 degrees Inclination: 57 degrees Orbits of Earth: 111 Orbits of Earth: 111 Orbits of Earth: 111

Y-17 Y-17 Y-17 61-A Mission Facts (Cont) 61-A Mission Facts (Cont) 61-A Mission Facts (Cont)

Orbital Altitude: 180 nautical miles (207 statute miles) Orbital Altitude: 180 nautical miles (207 statute miles) Orbital Altitude: 180 nautical miles (207 statute miles) circular circular circular Landing Touchdown: Approximately 1,829 feet beyond Landing Touchdown: Approximately 1,829 feet beyond Landing Touchdown: Approximately 1,829 feet beyond threshold threshold threshold Landing Rollout: Approximately 8,304 feet Landing Rollout: Approximately 8,304 feet Landing Rollout: Approximately 8,304 feet Orbiter Weight at Landing: Approximately 214,171 Orbiter Weight at Landing: Approximately 214,171 Orbiter Weight at Landing: Approximately 214,171 pounds pounds pounds Lift-off Weight: Approximately 4,508,496 pounds Lift-off Weight: Approximately 4,508,496 pounds Lift-off Weight: Approximately 4,508,496 pounds Payload Weight Up: Approximately 31,861 pounds Payload Weight Up: Approximately 31,861 pounds Payload Weight Up: Approximately 31,861 pounds Payload Weight Down: Approximately 31,711 pounds Payload Weight Down: Approximately 31,711 pounds Payload Weight Down: Approximately 31,711 pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 203 knots (233 miles per hour) mately 203 knots (233 miles per hour) mately 203 knots (233 miles per hour) Orbiter Weight at Lift-off: Approximately 243,762 Orbiter Weight at Lift-off: Approximately 243,762 Orbiter Weight at Lift-off: Approximately 243,762 pounds pounds pounds Landed: Runway 17 dry lake bed at Edwards Air Force Landed: Runway 17 dry lake bed at Edwards Air Force Landed: Runway 17 dry lake bed at Edwards Air Force Base, California Base, California Base, California Payload: Spacelab D-1 with habitable module and 76 Payload: Spacelab D-1 with habitable module and 76 Payload: Spacelab D-1 with habitable module and 76 experiments. Six of the eight crew members were experiments. Six of the eight crew members were experiments. Six of the eight crew members were divided into a blue and red team working 12-hour divided into a blue and red team working 12-hour divided into a blue and red team working 12-hour shifts for 24-hour-a-day operation. The remaining shifts for 24-hour-a-day operation. The remaining shifts for 24-hour-a-day operation. The remaining two crew members were “switch hitters.” two crew members were “switch hitters.” two crew members were “switch hitters.”

61-B Mission Facts — Atlantis — 61-B Mission Facts — Atlantis — 61-B Mission Facts — Atlantis — November 26–December 3, 1985 November 26–December 3, 1985 November 26–December 3, 1985

Commander: Brewster A. Shaw Commander: Brewster A. Shaw Commander: Brewster A. Shaw Pilot: Bryan D. O’Conner Pilot: Bryan D. O’Conner Pilot: Bryan D. O’Conner Mission Specialist: Sherwood C. Spring Mission Specialist: Sherwood C. Spring Mission Specialist: Sherwood C. Spring Mission Specialist: Mary L. Cleave Mission Specialist: Mary L. Cleave Mission Specialist: Mary L. Cleave Mission Specialist: Jerry L. Ross Mission Specialist: Jerry L. Ross Mission Specialist: Jerry L. Ross Payload Specialist: Charles D. Walker Payload Specialist: Charles D. Walker Payload Specialist: Charles D. Walker (McDonnell Douglas) (McDonnell Douglas) (McDonnell Douglas) Payload Specialist: Rodolfo Neri Vela (Mexico) Payload Specialist: Rodolfo Neri Vela (Mexico) Payload Specialist: Rodolfo Neri Vela (Mexico) Mission Duration: 144 hours (6 days), 21 hours, Mission Duration: 144 hours (6 days), 21 hours, Mission Duration: 144 hours (6 days), 21 hours, 4 minutes, 49 seconds 4 minutes, 49 seconds 4 minutes, 49 seconds Miles Traveled: Approximately 2,838,972 statute miles Miles Traveled: Approximately 2,838,972 statute miles Miles Traveled: Approximately 2,838,972 statute miles Inclination: 28.45 degrees Inclination: 28.45 degrees Inclination: 28.45 degrees Orbits of Earth: 108 Orbits of Earth: 108 Orbits of Earth: 108 Orbital Altitude: 190 by 190 nautical miles (218 by 218 Orbital Altitude: 190 by 190 nautical miles (218 by 218 Orbital Altitude: 190 by 190 nautical miles (218 by 218 statute miles), 190 by 195 nautical miles (218 by statute miles), 190 by 195 nautical miles (218 by statute miles), 190 by 195 nautical miles (218 by 224 statute miles), 196 by 195 nautical miles (225 224 statute miles), 196 by 195 nautical miles (225 224 statute miles), 196 by 195 nautical miles (225 by 224 statute miles), 196 by 204 nautical miles by 224 statute miles), 196 by 204 nautical miles by 224 statute miles), 196 by 204 nautical miles (225 by 234 statute miles) (225 by 234 statute miles) (225 by 234 statute miles) Landing Touchdown: Approximately 2,386 feet beyond Landing Touchdown: Approximately 2,386 feet beyond Landing Touchdown: Approximately 2,386 feet beyond threshold threshold threshold Landing Rollout: Approximately 10,759 feet Landing Rollout: Approximately 10,759 feet Landing Rollout: Approximately 10,759 feet Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately 205,732 pounds 205,732 pounds 205,732 pounds Lift-off Weight: Approximately 4,514,530 pounds Lift-off Weight: Approximately 4,514,530 pounds Lift-off Weight: Approximately 4,514,530 pounds Payload Weight Up: Approximately 48,041 pounds Payload Weight Up: Approximately 48,041 pounds Payload Weight Up: Approximately 48,041 pounds Payload Weight Down: Approximately 20,464 pounds Payload Weight Down: Approximately 20,464 pounds Payload Weight Down: Approximately 20,464 pounds

Y-18 Y-18 Y-18 61-B Mission Facts (Cont) 61-B Mission Facts (Cont) 61-B Mission Facts (Cont)

Landing Speed at Touchdown: Approximately Landing Speed at Touchdown: Approximately Landing Speed at Touchdown: Approximately 189 knots (217 miles per hour) 189 knots (217 miles per hour) 189 knots (217 miles per hour) Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately 261,610 pounds 261,610 pounds 261,610 pounds Landed: Concrete runway 22 at Edwards Air Force Landed: Concrete runway 22 at Edwards Air Force Landed: Concrete runway 22 at Edwards Air Force Base, California Base, California Base, California Extravehicular Activity (EVA): Jerry Ross and Sher- Extravehicular Activity (EVA): Jerry Ross and Sher- Extravehicular Activity (EVA): Jerry Ross and Sher- wood Spring, EVA No. 1, duration 5 hours, 34 wood Spring, EVA No. 1, duration 5 hours, 34 wood Spring, EVA No. 1, duration 5 hours, 34 minutes. EVA No. 2, duration 6 hours, 46 minutes minutes. EVA No. 2, duration 6 hours, 46 minutes minutes. EVA No. 2, duration 6 hours, 46 minutes Payloads: Deploy SATCOM (RCA-Satellite Communica- Payloads: Deploy SATCOM (RCA-Satellite Communica- Payloads: Deploy SATCOM (RCA-Satellite Communica- tions) Ku-2 with Payload Assist Module (PAM)-D tions) Ku-2 with Payload Assist Module (PAM)-D tions) Ku-2 with Payload Assist Module (PAM)-D II. Deploy Morelos (Mexico communications II. Deploy Morelos (Mexico communications II. Deploy Morelos (Mexico communications satellite)-B with PAM-D. Deploy AUSSAT (Aus- satellite)-B with PAM-D. Deploy AUSSAT (Aus- satellite)-B with PAM-D. Deploy AUSSAT (Aus- tralian communications satellite)-2 with PAM-D. tralian communications satellite)-2 with PAM-D. tralian communications satellite)-2 with PAM-D. EASE/ACCESS (Assembly of Structures—As- EASE/ACCESS (Assembly of Structures—As- EASE/ACCESS (Assembly of Structures—As- sembly Concept for Construction of Erectable sembly Concept for Construction of Erectable sembly Concept for Construction of Erectable Space Structures) by extravehicular activity (EVA) Space Structures) by extravehicular activity (EVA) Space Structures) by extravehicular activity (EVA) astronauts, Continuous Flow Electrophoresis astronauts, Continuous Flow Electrophoresis astronauts, Continuous Flow Electrophoresis System (CFES), Diffusive Mixing of Organic Solu- System (CFES), Diffusive Mixing of Organic Solu- System (CFES), Diffusive Mixing of Organic Solu- tions (DMOS), IMAX camera, one getaway special tions (DMOS), IMAX camera, one getaway special tions (DMOS), IMAX camera, one getaway special (GAS), Linhof camera and Hasseblad camera (GAS), Linhof camera and Hasseblad camera (GAS), Linhof camera and Hasseblad camera

61-C Mission Facts — Columbia — 61-C Mission Facts — Columbia — 61-C Mission Facts — Columbia — January 12–18, 1986 January 12–18, 1986 January 12–18, 1986

Commander: Robert L. Gibson Commander: Robert L. Gibson Commander: Robert L. Gibson Pilot: Charles F. Bolden, Jr. Pilot: Charles F. Bolden, Jr. Pilot: Charles F. Bolden, Jr. Mission Specialist: George D. Nelson Mission Specialist: George D. Nelson Mission Specialist: George D. Nelson Mission Specialist: Steven A. Hawley Mission Specialist: Steven A. Hawley Mission Specialist: Steven A. Hawley Mission Specialist: Franklin R. Chang-Diaz Mission Specialist: Franklin R. Chang-Diaz Mission Specialist: Franklin R. Chang-Diaz Payload Specialist: Robert J. Cenker Payload Specialist: Robert J. Cenker Payload Specialist: Robert J. Cenker Payload Specialist: Rep. Bill Nelson Payload Specialist: Rep. Bill Nelson Payload Specialist: Rep. Bill Nelson Mission Duration: 144 hours (6 days), 2 hours, Mission Duration: 144 hours (6 days), 2 hours, Mission Duration: 144 hours (6 days), 2 hours, 3 minutes, 51 seconds 3 minutes, 51 seconds 3 minutes, 51 seconds Miles Traveled: Approximately 2,528,658 statute miles Miles Traveled: Approximately 2,528,658 statute miles Miles Traveled: Approximately 2,528,658 statute miles Inclination: 28.45 degrees Inclination: 28.45 degrees Inclination: 28.45 degrees Orbits of Earth: 97 Orbits of Earth: 97 Orbits of Earth: 97 Orbital Altitude: 185 nautical miles (212 statute miles) Orbital Altitude: 185 nautical miles (212 statute miles) Orbital Altitude: 185 nautical miles (212 statute miles) circular orbit circular orbit circular orbit Landing Touchdown: Approximately 1,525 feet beyond Landing Touchdown: Approximately 1,525 feet beyond Landing Touchdown: Approximately 1,525 feet beyond threshold threshold threshold Landing Rollout: Approximately 10,202 feet Landing Rollout: Approximately 10,202 feet Landing Rollout: Approximately 10,202 feet Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately 210,161 pounds 210,161 pounds 210,161 pounds Lift-off Weight: Approximately 4,509,360 pounds Lift-off Weight: Approximately 4,509,360 pounds Lift-off Weight: Approximately 4,509,360 pounds Payload Weight Up: Approximately 32,462 pounds Payload Weight Up: Approximately 32,462 pounds Payload Weight Up: Approximately 32,462 pounds Payload Weight Down: Approximately 20,111 pounds Payload Weight Down: Approximately 20,111 pounds Payload Weight Down: Approximately 20,111 pounds Landing Speed at Touchdown: Approximately Landing Speed at Touchdown: Approximately Landing Speed at Touchdown: Approximately 217 knots (249 miles per hour) 217 knots (249 miles per hour) 217 knots (249 miles per hour)

Y-19 Y-19 Y-19 61-C Mission Facts (Cont) 61-C Mission Facts (Cont) 61-C Mission Facts (Cont)

Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately 256,003 pounds 256,003 pounds 256,003 pounds Landed: Concrete runway 22 at Edwards Air Force Landed: Concrete runway 22 at Edwards Air Force Landed: Concrete runway 22 at Edwards Air Force Base, California Base, California Base, California Payloads: Deploy SATCOM (RCA-Satellite Communica- Payloads: Deploy SATCOM (RCA-Satellite Communica- Payloads: Deploy SATCOM (RCA-Satellite Communica- tions) Ku-1 with Payload Assist Module (PAM)-D tions) Ku-1 with Payload Assist Module (PAM)-D tions) Ku-1 with Payload Assist Module (PAM)-D II. Materials Science Laboratory, Comet Halley II. Materials Science Laboratory, Comet Halley II. Materials Science Laboratory, Comet Halley Active Monitoring Experiment (CHAMP), Hitchhiker Active Monitoring Experiment (CHAMP), Hitchhiker Active Monitoring Experiment (CHAMP), Hitchhiker (HH)—Goddard (G)-1, thirteen getaway specials (HH)—Goddard (G)-1, thirteen getaway specials (HH)—Goddard (G)-1, thirteen getaway specials (GAS), student experiment, Initial Blood Storage (GAS), student experiment, Initial Blood Storage (GAS), student experiment, Initial Blood Storage Equipment (lBSE), Characterization of Space Equipment (lBSE), Characterization of Space Equipment (lBSE), Characterization of Space Motion Sickness (SMS) Motion Sickness (SMS) Motion Sickness (SMS)

51-L Mission Facts — Challenger — 51-L Mission Facts — Challenger — 51-L Mission Facts — Challenger — January 28, 1986 January 28, 1986 January 28, 1986

Commander: Francis R. Scobee Commander: Francis R. Scobee Commander: Francis R. Scobee Pilot: Michael J. Smith Pilot: Michael J. Smith Pilot: Michael J. Smith Mission Specialist: Ellison S. Onizuka Mission Specialist: Ellison S. Onizuka Mission Specialist: Ellison S. Onizuka Mission Specialist: Judith A. Resnik Mission Specialist: Judith A. Resnik Mission Specialist: Judith A. Resnik Mission Specialist: Ronald E. McNair Mission Specialist: Ronald E. McNair Mission Specialist: Ronald E. McNair Payload Specialist: Gregory Jarvis (Hughes) Payload Specialist: Gregory Jarvis (Hughes) Payload Specialist: Gregory Jarvis (Hughes) Payload Specialist: Sharon Christa McAuliffe, Teacher Payload Specialist: Sharon Christa McAuliffe, Teacher Payload Specialist: Sharon Christa McAuliffe, Teacher In Space In Space In Space Inclination: 28.45 degrees Inclination: 28.45 degrees Inclination: 28.45 degrees Lift-off Weight: Approximately 4,526,583 pounds Lift-off Weight: Approximately 4,526,583 pounds Lift-off Weight: Approximately 4,526,583 pounds Total Payload Weight Up: Approximately 52,308 Total Payload Weight Up: Approximately 52,308 Total Payload Weight Up: Approximately 52,308 pounds pounds pounds Orbiter Weight at Lift-off: Approximately 268,829 Orbiter Weight at Lift-off: Approximately 268,829 Orbiter Weight at Lift-off: Approximately 268,829 pounds pounds pounds Payloads: Tracking Data Relay Satellite (TDRS)-B, Payloads: Tracking Data Relay Satellite (TDRS)-B, Payloads: Tracking Data Relay Satellite (TDRS)-B, SPARTAN-203 Halley’s Comet Experiment, SPARTAN-203 Halley’s Comet Experiment, SPARTAN-203 Halley’s Comet Experiment, Teacher in Space Project, Fluid Dynamics Teacher in Space Project, Fluid Dynamics Teacher in Space Project, Fluid Dynamics Experiment, Comet Halley Active Monitoring Experiment, Comet Halley Active Monitoring Experiment, Comet Halley Active Monitoring Program, Phase Partitioning Experiment (PPE), Program, Phase Partitioning Experiment (PPE), Program, Phase Partitioning Experiment (PPE), Radiation Monitoring Experiment (RME), three Radiation Monitoring Experiment (RME), three Radiation Monitoring Experiment (RME), three Shuttle Student Involvement Program experiments Shuttle Student Involvement Program experiments Shuttle Student Involvement Program experiments Loss of vehicle and crew Loss of vehicle and crew Loss of vehicle and crew

STS-26 Mission Facts — Discovery — STS-26 Mission Facts — Discovery — STS-26 Mission Facts — Discovery — September 29–October 3, 1988 September 29–October 3, 1988 September 29–October 3, 1988

Commander: Frederick H. Hauck Commander: Frederick H. Hauck Commander: Frederick H. Hauck Pilot: Richard O. Covey Pilot: Richard O. Covey Pilot: Richard O. Covey Mission Specialist: John M. Lounge Mission Specialist: John M. Lounge Mission Specialist: John M. Lounge Mission Specialist: George D. Nelson Mission Specialist: George D. Nelson Mission Specialist: George D. Nelson Mission Specialist: David C. Hilmers Mission Specialist: David C. Hilmers Mission Specialist: David C. Hilmers

Y-20 Y-20 Y-20 STS-26 Mission Facts (Cont) STS-26 Mission Facts (Cont) STS-26 Mission Facts (Cont)

Mission Duration: 96 hours (4 days), 1 hour, 11 seconds Mission Duration: 96 hours (4 days), 1 hour, 11 seconds Mission Duration: 96 hours (4 days), 1 hour, 11 seconds Miles Traveled: Approximately 1.68 million statute miles Miles Traveled: Approximately 1.68 million statute miles Miles Traveled: Approximately 1.68 million statute miles Inclination: 28.5 degrees Inclination: 28.5 degrees Inclination: 28.5 degrees Orbits of Earth: 63 Orbits of Earth: 63 Orbits of Earth: 63 Orbital Altitude: 163 by 159 nautical miles (187 by 182 Orbital Altitude: 163 by 159 nautical miles (187 by 182 Orbital Altitude: 163 by 159 nautical miles (187 by 182 statute miles), 177 by 162 nautical miles (203 by statute miles), 177 by 162 nautical miles (203 by statute miles), 177 by 162 nautical miles (203 by 186 statute miles) 186 statute miles) 186 statute miles) Landing Touchdown: Approximately 2,500 feet beyond Landing Touchdown: Approximately 2,500 feet beyond Landing Touchdown: Approximately 2,500 feet beyond threshold threshold threshold Landing Rollout: Approximately 7,451 feet Landing Rollout: Approximately 7,451 feet Landing Rollout: Approximately 7,451 feet Orbiter Weight at Landing: Approximately 194,184 Orbiter Weight at Landing: Approximately 194,184 Orbiter Weight at Landing: Approximately 194,184 pounds pounds pounds Lift-off Weight: Approximately 4,522,411 pounds Lift-off Weight: Approximately 4,522,411 pounds Lift-off Weight: Approximately 4,522,411 pounds Payload Weight Up: Approximately 46,478 pounds Payload Weight Up: Approximately 46,478 pounds Payload Weight Up: Approximately 46,478 pounds Payload Weight Down: Approximately 8,964 pounds Payload Weight Down: Approximately 8,964 pounds Payload Weight Down: Approximately 8,964 pounds Landing Speed at Touchdown: Approximately 187 Landing Speed at Touchdown: Approximately 187 Landing Speed at Touchdown: Approximately 187 knots (215 miles per hour) knots (215 miles per hour) knots (215 miles per hour) Orbiter Weight at Lift-off: Approximately 254,606 Orbiter Weight at Lift-off: Approximately 254,606 Orbiter Weight at Lift-off: Approximately 254,606 pounds pounds pounds Landed: Runway 17 dry lake bed at Edwards Air Force Landed: Runway 17 dry lake bed at Edwards Air Force Landed: Runway 17 dry lake bed at Edwards Air Force Base, California Base, California Base, California Payloads: Deploy IUS (lnertial Upper Stage) with Payloads: Deploy IUS (lnertial Upper Stage) with Payloads: Deploy IUS (lnertial Upper Stage) with Tracking and Data Relay Satellite (TDRS)-C. 3M’s Tracking and Data Relay Satellite (TDRS)-C. 3M’s Tracking and Data Relay Satellite (TDRS)-C. 3M’s Physical Vapor Transport Organics Solids 2 experi- Physical Vapor Transport Organics Solids 2 experi- Physical Vapor Transport Organics Solids 2 experi- ment (PVTOS), Automated Directional Solidifica- ment (PVTOS), Automated Directional Solidifica- ment (PVTOS), Automated Directional Solidifica- tion Furnace (ADSF), Infrared Communications tion Furnace (ADSF), Infrared Communications tion Furnace (ADSF), Infrared Communications Flight Experiment (lRCFE), Protein Crystal Growth Flight Experiment (lRCFE), Protein Crystal Growth Flight Experiment (lRCFE), Protein Crystal Growth Il (PCG), Isoelectric Focusing (ISF)-2, Phase Par- Il (PCG), Isoelectric Focusing (ISF)-2, Phase Par- Il (PCG), Isoelectric Focusing (ISF)-2, Phase Par- titioning Experiment (PPE), Aggregation of Red titioning Experiment (PPE), Aggregation of Red titioning Experiment (PPE), Aggregation of Red Blood Cells (ARC)-2, Mesoscale Lightning Blood Cells (ARC)-2, Mesoscale Lightning Blood Cells (ARC)-2, Mesoscale Lightning Experiment (MLE)-1, Earth Limb Radiance Experiment (MLE)-1, Earth Limb Radiance Experiment (MLE)-1, Earth Limb Radiance (ELRAD), Orbiter Experiments (OEX), Autonomous (ELRAD), Orbiter Experiments (OEX), Autonomous (ELRAD), Orbiter Experiments (OEX), Autonomous Supporting Instrumentation System (OASlS)-I, two Supporting Instrumentation System (OASlS)-I, two Supporting Instrumentation System (OASlS)-I, two Shuttle Student Involvement Project (SSIP) Shuttle Student Involvement Project (SSIP) Shuttle Student Involvement Project (SSIP) experiments experiments experiments

STS-27 Mission Facts — Atlantis — STS-27 Mission Facts — Atlantis — STS-27 Mission Facts — Atlantis — December 2–6, 1988 December 2–6, 1988 December 2–6, 1988

Commander: Robert L. Gibson Commander: Robert L. Gibson Commander: Robert L. Gibson Pilot: Guy S. Gardner Pilot: Guy S. Gardner Pilot: Guy S. Gardner Mission Specialist: Richard M. Mullane Mission Specialist: Richard M. Mullane Mission Specialist: Richard M. Mullane Mission Specialist: Jerry L. Ross Mission Specialist: Jerry L. Ross Mission Specialist: Jerry L. Ross Mission Specialist: William M. Shepherd Mission Specialist: William M. Shepherd Mission Specialist: William M. Shepherd Mission Duration: 96 hours (4 days), 9 hours, Mission Duration: 96 hours (4 days), 9 hours, Mission Duration: 96 hours (4 days), 9 hours, 5 minutes, 35 seconds 5 minutes, 35 seconds 5 minutes, 35 seconds Orbits of Earth: 68 Orbits of Earth: 68 Orbits of Earth: 68 Inclination: 57 degrees Inclination: 57 degrees Inclination: 57 degrees Landing Speed at Touchdown: 194 knots Landing Speed at Touchdown: 194 knots Landing Speed at Touchdown: 194 knots (223 miles per hour) (223 miles per hour) (223 miles per hour)

Y-21 Y-21 Y-21 STS-27 Mission Facts (Cont) STS-27 Mission Facts (Cont) STS-27 Mission Facts (Cont)

Landing Touchdown: Approximately 1,469 feet beyond Landing Touchdown: Approximately 1,469 feet beyond Landing Touchdown: Approximately 1,469 feet beyond threshold threshold threshold Landing Rollout: Approximately 7,123 feet Landing Rollout: Approximately 7,123 feet Landing Rollout: Approximately 7,123 feet Landed: Runway 17 dry lake bed at Edwards Air Force Landed: Runway 17 dry lake bed at Edwards Air Force Landed: Runway 17 dry lake bed at Edwards Air Force Base, California Base, California Base, California Payload: DOD Payload: DOD Payload: DOD

STS-29 Mission Facts — Discovery — STS-29 Mission Facts — Discovery — STS-29 Mission Facts — Discovery — March 13–18, 1989 March 13–18, 1989 March 13–18, 1989

Commander: Michael L. Coats Commander: Michael L. Coats Commander: Michael L. Coats Pilot: John E. Blaha Pilot: John E. Blaha Pilot: John E. Blaha Mission Specialist: James F. Buchli Mission Specialist: James F. Buchli Mission Specialist: James F. Buchli Mission Specialist: Robert C. Springer Mission Specialist: Robert C. Springer Mission Specialist: Robert C. Springer Mission Specialist: James P. Bagian Mission Specialist: James P. Bagian Mission Specialist: James P. Bagian Mission Duration: 96 hours (4 days), 23 hours, Mission Duration: 96 hours (4 days), 23 hours, Mission Duration: 96 hours (4 days), 23 hours, 38 minutes, 52 seconds 38 minutes, 52 seconds 38 minutes, 52 seconds Miles Traveled: Approximately 2 million statute miles Miles Traveled: Approximately 2 million statute miles Miles Traveled: Approximately 2 million statute miles Inclination: 28.45 degrees Inclination: 28.45 degrees Inclination: 28.45 degrees Orbits of Earth: 79 Orbits of Earth: 79 Orbits of Earth: 79 Orbital Altitude: 160 nautical miles (184 statute miles), Orbital Altitude: 160 nautical miles (184 statute miles), Orbital Altitude: 160 nautical miles (184 statute miles), 160 by 177 nautical miles (184 by 203 statute 160 by 177 nautical miles (184 by 203 statute 160 by 177 nautical miles (184 by 203 statute miles) miles) miles) Landing Touchdown: Approximately 1,195 feet beyond Landing Touchdown: Approximately 1,195 feet beyond Landing Touchdown: Approximately 1,195 feet beyond threshold threshold threshold Landing Rollout: Approximately 9,339 feet Landing Rollout: Approximately 9,339 feet Landing Rollout: Approximately 9,339 feet Orbiter Weight at Landing: Approximately 194,789 Orbiter Weight at Landing: Approximately 194,789 Orbiter Weight at Landing: Approximately 194,789 pounds pounds pounds Lift-off Weight: Approximately 4,524,261 pounds Lift-off Weight: Approximately 4,524,261 pounds Lift-off Weight: Approximately 4,524,261 pounds Payload Weight Up: Approximately 38,097 pounds Payload Weight Up: Approximately 38,097 pounds Payload Weight Up: Approximately 38,097 pounds Payload Weight Down: Approximately 9,861 pounds Payload Weight Down: Approximately 9,861 pounds Payload Weight Down: Approximately 9,861 pounds Landing Speed at Touchdown: Approximately 205 Landing Speed at Touchdown: Approximately 205 Landing Speed at Touchdown: Approximately 205 knots (235 miles per hour) knots (235 miles per hour) knots (235 miles per hour) Orbiter Weight at Lift-off: Approximately 256,357 Orbiter Weight at Lift-off: Approximately 256,357 Orbiter Weight at Lift-off: Approximately 256,357 pounds pounds pounds Landed: Concrete runway 22 at Edwards AFB, California Landed: Concrete runway 22 at Edwards AFB, California Landed: Concrete runway 22 at Edwards AFB, California Payloads: Deploy IUS (Inertial Upper Stage) with Track- Payloads: Deploy IUS (Inertial Upper Stage) with Track- Payloads: Deploy IUS (Inertial Upper Stage) with Track- ing and Data Relay Satellite (TDRS)-D. Protein ing and Data Relay Satellite (TDRS)-D. Protein ing and Data Relay Satellite (TDRS)-D. Protein Crystal Growth (PCG); Chromosome and Plant Crystal Growth (PCG); Chromosome and Plant Crystal Growth (PCG); Chromosome and Plant Cell Division in Space; IMAX 70mm camera; Cell Division in Space; IMAX 70mm camera; Cell Division in Space; IMAX 70mm camera; Shuttle Student Involvement Project (SSIP) experi- Shuttle Student Involvement Project (SSIP) experi- Shuttle Student Involvement Project (SSIP) experi- ments: SSIP 82-8, Effects of Weightlessness in ments: SSIP 82-8, Effects of Weightlessness in ments: SSIP 82-8, Effects of Weightlessness in Space Flight on the Healing of Bone Fractures, Space Flight on the Healing of Bone Fractures, Space Flight on the Healing of Bone Fractures, and SSIP 83-9, Chicken Embryo Development in and SSIP 83-9, Chicken Embryo Development in and SSIP 83-9, Chicken Embryo Development in Space; Air Force Maui Optical Site (AMOS) Space; Air Force Maui Optical Site (AMOS) Space; Air Force Maui Optical Site (AMOS) experiment. experiment. experiment.

Y-22 Y-22 Y-22 STS-30 Mission Facts — Atlantis — STS-30 Mission Facts — Atlantis — STS-30 Mission Facts — Atlantis — May 4–8, 1989 May 4–8, 1989 May 4–8, 1989 Commander: David M. Walker Commander: David M. Walker Commander: David M. Walker Pilot: Ronald J. Grabe Pilot: Ronald J. Grabe Pilot: Ronald J. Grabe Mission Specialist: Norman E. Thagard Mission Specialist: Norman E. Thagard Mission Specialist: Norman E. Thagard Mission Specialist: Mary L. Cleave Mission Specialist: Mary L. Cleave Mission Specialist: Mary L. Cleave Mission Specialist: Mark C. Lee Mission Specialist: Mark C. Lee Mission Specialist: Mark C. Lee Mission Duration: 96 hours (4 days), 57 minutes, Mission Duration: 96 hours (4 days), 57 minutes, Mission Duration: 96 hours (4 days), 57 minutes, 31 seconds 31 seconds 31 seconds Miles Traveled: 1,681,997 statute miles Miles Traveled: 1,681,997 statute miles Miles Traveled: 1,681,997 statute miles Inclination: 28.85 degrees Inclination: 28.85 degrees Inclination: 28.85 degrees Orbits of Earth: 64 Orbits of Earth: 64 Orbits of Earth: 64 Orbital Altitude: 4 by 85 nautical miles (4.6 by 97 statute Orbital Altitude: 4 by 85 nautical miles (4.6 by 97 statute Orbital Altitude: 4 by 85 nautical miles (4.6 by 97 statute miles), 51 by 161 nautical miles (58 by 185 statute miles), 51 by 161 nautical miles (58 by 185 statute miles), 51 by 161 nautical miles (58 by 185 statute miles), 160 by 161 nautical miles (184 by 185 stat- miles), 160 by 161 nautical miles (184 by 185 stat- miles), 160 by 161 nautical miles (184 by 185 stat- ute miles), 160 by 177 nautical miles (184 by 203 ute miles), 160 by 177 nautical miles (184 by 203 ute miles), 160 by 177 nautical miles (184 by 203 statute miles) statute miles) statute miles) Landing Touchdown: Approximately 1,382 feet beyond Landing Touchdown: Approximately 1,382 feet beyond Landing Touchdown: Approximately 1,382 feet beyond threshold threshold threshold Landing Rollout: Approximately 10,295 feet Landing Rollout: Approximately 10,295 feet Landing Rollout: Approximately 10,295 feet Orbiter Weight at Landing: Approximately 192,459 Orbiter Weight at Landing: Approximately 192,459 Orbiter Weight at Landing: Approximately 192,459 pounds pounds pounds Lift-off Weight: Approximately 4,527,426 pounds Lift-off Weight: Approximately 4,527,426 pounds Lift-off Weight: Approximately 4,527,426 pounds Payload Weight Up: Approximately 45,930 pounds Payload Weight Up: Approximately 45,930 pounds Payload Weight Up: Approximately 45,930 pounds Payload Weight Down: Approximately 7,701 pounds Payload Weight Down: Approximately 7,701 pounds Payload Weight Down: Approximately 7,701 pounds Orbiter Weight at Lift-off: Approximately 261,118 Orbiter Weight at Lift-off: Approximately 261,118 Orbiter Weight at Lift-off: Approximately 261,118 pounds pounds pounds Landing Speed at Touchdown: Approximately 196 Landing Speed at Touchdown: Approximately 196 Landing Speed at Touchdown: Approximately 196 knots (225 miles per hour) knots (225 miles per hour) knots (225 miles per hour) Landed: Concrete runway 22 at Edwards AFB, Landed: Concrete runway 22 at Edwards AFB, Landed: Concrete runway 22 at Edwards AFB, California California California Payloads: Deploy IUS with Magellan spacecraft. Fluids Payloads: Deploy IUS with Magellan spacecraft. Fluids Payloads: Deploy IUS with Magellan spacecraft. Fluids Experiment Apparatus (FEA). Mesoscale Lightning Experiment Apparatus (FEA). Mesoscale Lightning Experiment Apparatus (FEA). Mesoscale Lightning Experiment (MLE), Air Force Maui Optical Site Experiment (MLE), Air Force Maui Optical Site Experiment (MLE), Air Force Maui Optical Site (AMOS) experiment (AMOS) experiment (AMOS) experiment STS-28 Mission Facts — Columbia — STS-28 Mission Facts — Columbia — STS-28 Mission Facts — Columbia — August 8–13, 1989 August 8–13, 1989 August 8–13, 1989

Commander: Brewster H. Shaw Commander: Brewster H. Shaw Commander: Brewster H. Shaw Pilot: Richard N. Richards Pilot: Richard N. Richards Pilot: Richard N. Richards Mission Specialist: David C. Leestma Mission Specialist: David C. Leestma Mission Specialist: David C. Leestma Mission Specialist: James C. Adamson Mission Specialist: James C. Adamson Mission Specialist: James C. Adamson Mission Specialist: Mark N. Brown Mission Specialist: Mark N. Brown Mission Specialist: Mark N. Brown Mission Duration: 120 hours (5 days), 1 hour, Mission Duration: 120 hours (5 days), 1 hour, Mission Duration: 120 hours (5 days), 1 hour, 9 seconds 9 seconds 9 seconds Inclination: 57 degrees Inclination: 57 degrees Inclination: 57 degrees Landing Speed at Touchdown: Approximately Landing Speed at Touchdown: Approximately Landing Speed at Touchdown: Approximately 155 knots (178 miles per hour) 155 knots (178 miles per hour) 155 knots (178 miles per hour) Landing Touchdown: Approximately 5,311 feet beyond Landing Touchdown: Approximately 5,311 feet beyond Landing Touchdown: Approximately 5,311 feet beyond threshold threshold threshold Landing Rollout: Approximately 6,015 feet Landing Rollout: Approximately 6,015 feet Landing Rollout: Approximately 6,015 feet Landed: Runway 17 dry lake bed at Edwards Air Landed: Runway 17 dry lake bed at Edwards Air Landed: Runway 17 dry lake bed at Edwards Air Force Base, California Force Base, California Force Base, California Payload: DOD Payload: DOD Payload: DOD Y-23 Y-23 Y-23 STS-34 Mission Facts — Atlantis — STS-34 Mission Facts — Atlantis — STS-34 Mission Facts — Atlantis — October 18–23, 1989 October 18–23, 1989 October 18–23, 1989

Commander: Donald E. Williams Commander: Donald E. Williams Commander: Donald E. Williams Pilot: Michael J. McCulley Pilot: Michael J. McCulley Pilot: Michael J. McCulley Mission Specialist: Shannon W. Lucid Mission Specialist: Shannon W. Lucid Mission Specialist: Shannon W. Lucid Mission Specialist: Ellen S. Baker Mission Specialist: Ellen S. Baker Mission Specialist: Ellen S. Baker Mission Specialist: Franklin R. Chang-Diaz Mission Specialist: Franklin R. Chang-Diaz Mission Specialist: Franklin R. Chang-Diaz Mission Duration: 96 hours (4 days), 23 hours, Mission Duration: 96 hours (4 days), 23 hours, Mission Duration: 96 hours (4 days), 23 hours, 39 minutes, 24 seconds 39 minutes, 24 seconds 39 minutes, 24 seconds Miles Traveled: 2 million statute miles Miles Traveled: 2 million statute miles Miles Traveled: 2 million statute miles Inclination: 34.30 degrees; first flight at this inclination Inclination: 34.30 degrees; first flight at this inclination Inclination: 34.30 degrees; first flight at this inclination Orbits of Earth: 79 Orbits of Earth: 79 Orbits of Earth: 79 Orbital Altitude: 156 by 39 nautical miles (179 by 44 Orbital Altitude: 156 by 39 nautical miles (179 by 44 Orbital Altitude: 156 by 39 nautical miles (179 by 44 statute miles), 160 by 161 nautical miles (184 by statute miles), 160 by 161 nautical miles (184 by statute miles), 160 by 161 nautical miles (184 by 185 statute miles), 161 by 179 nautical miles 185 statute miles), 161 by 179 nautical miles 185 statute miles), 161 by 179 nautical miles (185 by 205 statute miles) (185 by 205 statute miles) (185 by 205 statute miles) Landing Rollout: Approximately 9,677 feet Landing Rollout: Approximately 9,677 feet Landing Rollout: Approximately 9,677 feet Orbiter Weight at Landing: Approximately 195,954 Orbiter Weight at Landing: Approximately 195,954 Orbiter Weight at Landing: Approximately 195,954 pounds pounds pounds Lift-off Weight: Approximately 4,524,224 pounds Lift-off Weight: Approximately 4,524,224 pounds Lift-off Weight: Approximately 4,524,224 pounds Payload Weight Up: Approximately 48,643 pounds Payload Weight Up: Approximately 48,643 pounds Payload Weight Up: Approximately 48,643 pounds Payload Weight Down: Approximately 10,625 pounds Payload Weight Down: Approximately 10,625 pounds Payload Weight Down: Approximately 10,625 pounds Orbiter Weight at Lift-off: Approximately 257,569 Orbiter Weight at Lift-off: Approximately 257,569 Orbiter Weight at Lift-off: Approximately 257,569 pounds pounds pounds Landing Speed at Touchdown: Approximately Landing Speed at Touchdown: Approximately Landing Speed at Touchdown: Approximately 195 knots (224 miles per hour) 195 knots (224 miles per hour) 195 knots (224 miles per hour) Landed: Runway 23 dry lake bed at Edwards Air Force Landed: Runway 23 dry lake bed at Edwards Air Force Landed: Runway 23 dry lake bed at Edwards Air Force Base, California Base, California Base, California Payloads: Deploy IUS with Galileo spacecraft. Shuttle Payloads: Deploy IUS with Galileo spacecraft. Shuttle Payloads: Deploy IUS with Galileo spacecraft. Shuttle Solar Backscatter Ultraviolet (SSBUV), Polymer Solar Backscatter Ultraviolet (SSBUV), Polymer Solar Backscatter Ultraviolet (SSBUV), Polymer Morphology (PM) experiments, IMAX camera Morphology (PM) experiments, IMAX camera Morphology (PM) experiments, IMAX camera project, Mesoscale Lightning Experiment (MLE), project, Mesoscale Lightning Experiment (MLE), project, Mesoscale Lightning Experiment (MLE), Air Force Maui Optical Site (AMOS) experiment, Air Force Maui Optical Site (AMOS) experiment, Air Force Maui Optical Site (AMOS) experiment, Growth Hormone Concentration and Distribution Growth Hormone Concentration and Distribution Growth Hormone Concentration and Distribution (GHCD) in Plants experiment, Sensor Technology (GHCD) in Plants experiment, Sensor Technology (GHCD) in Plants experiment, Sensor Technology Experiment (STEX), SSIP Student Experiment (SE) Experiment (STEX), SSIP Student Experiment (SE) Experiment (STEX), SSIP Student Experiment (SE) 82-15, Ice Crystals Experiment 82-15, Ice Crystals Experiment 82-15, Ice Crystals Experiment

STS-33 Mission Facts — Discovery — STS-33 Mission Facts — Discovery — STS-33 Mission Facts — Discovery — November 22–27, 1989 November 22–27, 1989 November 22–27, 1989

Commander: Frederick D. Gregory Commander: Frederick D. Gregory Commander: Frederick D. Gregory Pilot: John E. Blaha Pilot: John E. Blaha Pilot: John E. Blaha Mission Specialist: F. Story Musgrave Mission Specialist: F. Story Musgrave Mission Specialist: F. Story Musgrave Mission Specialist: Kathryn C. Thornton Mission Specialist: Kathryn C. Thornton Mission Specialist: Kathryn C. Thornton Mission Specialist: Manley L. Carter, Jr. Mission Specialist: Manley L. Carter, Jr. Mission Specialist: Manley L. Carter, Jr. Mission Duration: 120 hours (5 days), 6 minutes, Mission Duration: 120 hours (5 days), 6 minutes, Mission Duration: 120 hours (5 days), 6 minutes, 49 seconds 49 seconds 49 seconds Miles Traveled: 2 million statute miles Miles Traveled: 2 million statute miles Miles Traveled: 2 million statute miles Inclination: 28.45 degrees Inclination: 28.45 degrees Inclination: 28.45 degrees Orbits of Earth: 78 Orbits of Earth: 78 Orbits of Earth: 78 Landing Speed at Touchdown: Approximately Landing Speed at Touchdown: Approximately Landing Speed at Touchdown: Approximately 199 knots (229 miles per hour) 199 knots (229 miles per hour) 199 knots (229 miles per hour)

Y-24 Y-24 Y-24 STS-33 Mission Facts (Cont) STS-33 Mission Facts (Cont) STS-33 Mission Facts (Cont)

Landing Touchdown: Approximately 1,871 feet beyond Landing Touchdown: Approximately 1,871 feet beyond Landing Touchdown: Approximately 1,871 feet beyond threshold threshold threshold Landing Rollout: Approximately 7,764 feet Landing Rollout: Approximately 7,764 feet Landing Rollout: Approximately 7,764 feet Landed: Concrete runway 04 at Edwards Air Force Landed: Concrete runway 04 at Edwards Air Force Landed: Concrete runway 04 at Edwards Air Force Base, California Base, California Base, California Payload: DOD Payload: DOD Payload: DOD This was the third Space Shuttle night launch. This was the third Space Shuttle night launch. This was the third Space Shuttle night launch.

STS-32 Mission Facts — Columbia — STS-32 Mission Facts — Columbia — STS-32 Mission Facts — Columbia — January 9–20, 1990 January 9–20, 1990 January 9–20, 1990

Commander: Daniel C. Brandenstein Commander: Daniel C. Brandenstein Commander: Daniel C. Brandenstein Pilot: James D. Wetherbee Pilot: James D. Wetherbee Pilot: James D. Wetherbee Mission Specialist: Bonnie J. Dunbar Mission Specialist: Bonnie J. Dunbar Mission Specialist: Bonnie J. Dunbar Mission Specialist: G. David Low Mission Specialist: G. David Low Mission Specialist: G. David Low Mission Specialist: Marsha S. lvins Mission Specialist: Marsha S. lvins Mission Specialist: Marsha S. lvins Mission Duration: 240 hours (10 days), 21 hours, Mission Duration: 240 hours (10 days), 21 hours, Mission Duration: 240 hours (10 days), 21 hours, 37 seconds 37 seconds 37 seconds Miles Traveled: 4,509,972 statute miles Miles Traveled: 4,509,972 statute miles Miles Traveled: 4,509,972 statute miles Inclination: 28.5 degrees Inclination: 28.5 degrees Inclination: 28.5 degrees Orbits of Earth: 171 Orbits of Earth: 171 Orbits of Earth: 171 Orbital Altitude: (Approximation due to rendezvous Orbital Altitude: (Approximation due to rendezvous Orbital Altitude: (Approximation due to rendezvous sequence in real time) 193 by 155 nautical miles sequence in real time) 193 by 155 nautical miles sequence in real time) 193 by 155 nautical miles (222 by 178 statute miles), 194 by 156 nautical (222 by 178 statute miles), 194 by 156 nautical (222 by 178 statute miles), 194 by 156 nautical miles (233 by 179 statute miles), 183 by 169 nauti- miles (233 by 179 statute miles), 183 by 169 nauti- miles (233 by 179 statute miles), 183 by 169 nauti- cal miles (210 by 194 statute miles), 184 by 177 cal miles (210 by 194 statute miles), 184 by 177 cal miles (210 by 194 statute miles), 184 by 177 nautical miles (211 by 203 statute miles), 181 by nautical miles (211 by 203 statute miles), 181 by nautical miles (211 by 203 statute miles), 181 by 176 nautical miles (208 by 202 statute miles), 181 176 nautical miles (208 by 202 statute miles), 181 176 nautical miles (208 by 202 statute miles), 181 by 175 nautical miles (208 by 201 statute miles) by 175 nautical miles (208 by 201 statute miles) by 175 nautical miles (208 by 201 statute miles) Landing Rollout: Approximately 10,731 feet Landing Rollout: Approximately 10,731 feet Landing Rollout: Approximately 10,731 feet Landing Touchdown: 1,870 feet beyond threshold Landing Touchdown: 1,870 feet beyond threshold Landing Touchdown: 1,870 feet beyond threshold Orbiter Weight at Landing: Approximately 228,335 Orbiter Weight at Landing: Approximately 228,335 Orbiter Weight at Landing: Approximately 228,335 pounds pounds pounds Lift-off Weight: Approximately 4,519,487 pounds Lift-off Weight: Approximately 4,519,487 pounds Lift-off Weight: Approximately 4,519,487 pounds Payload Weight Up: Approximately 26,488 pounds Payload Weight Up: Approximately 26,488 pounds Payload Weight Up: Approximately 26,488 pounds Payload Weight Down: Approximately 21,393 pounds Payload Weight Down: Approximately 21,393 pounds Payload Weight Down: Approximately 21,393 pounds Orbiter Weight at Lift-off: Approximately 255,994 Orbiter Weight at Lift-off: Approximately 255,994 Orbiter Weight at Lift-off: Approximately 255,994 pounds pounds pounds Landing Speed at Touchdown: Approximately 207 Landing Speed at Touchdown: Approximately 207 Landing Speed at Touchdown: Approximately 207 knots (238 miles per hour) knots (238 miles per hour) knots (238 miles per hour) Landed: Concrete runway 22 at Edwards Air Force Landed: Concrete runway 22 at Edwards Air Force Landed: Concrete runway 22 at Edwards Air Force Base, California (night landing) Base, California (night landing) Base, California (night landing) Payloads: Deployment of Syncom IV-5, retrieval of Long Payloads: Deployment of Syncom IV-5, retrieval of Long Payloads: Deployment of Syncom IV-5, retrieval of Long Duration Exposure Facility (LDEF), Fluids Experi- Duration Exposure Facility (LDEF), Fluids Experi- Duration Exposure Facility (LDEF), Fluids Experi- ment Apparatus (FEA)-3, Protein Crystal Growth ment Apparatus (FEA)-3, Protein Crystal Growth ment Apparatus (FEA)-3, Protein Crystal Growth (PCG) III-2, Latitude/Longitude Locator (L3), Amer- (PCG) III-2, Latitude/Longitude Locator (L3), Amer- (PCG) III-2, Latitude/Longitude Locator (L3), Amer- ican Flight Echocardiograph (AFE), Characteriza- ican Flight Echocardiograph (AFE), Characteriza- ican Flight Echocardiograph (AFE), Characteriza- tion of Neurospora Circadian Rhythms in Space tion of Neurospora Circadian Rhythms in Space tion of Neurospora Circadian Rhythms in Space (CNCR)-01, Air Force Maui Optical Site (AMOS)-4, (CNCR)-01, Air Force Maui Optical Site (AMOS)-4, (CNCR)-01, Air Force Maui Optical Site (AMOS)-4, Mesoscale Lightning Experiment (MLE), IMAX, Mesoscale Lightning Experiment (MLE), IMAX, Mesoscale Lightning Experiment (MLE), IMAX, Interim Operational Contamination Monitor (lOCM) Interim Operational Contamination Monitor (lOCM) Interim Operational Contamination Monitor (lOCM)

Y-25 Y-25 Y-25 STS-36 Mission Facts — Atlantis — STS-36 Mission Facts — Atlantis — STS-36 Mission Facts — Atlantis — February 28–March 4, 1990 February 28–March 4, 1990 February 28–March 4, 1990

Commander: John O. Creighton Commander: John O. Creighton Commander: John O. Creighton Pilot: John H. Casper Pilot: John H. Casper Pilot: John H. Casper Mission Specialist: David C. Hilmers Mission Specialist: David C. Hilmers Mission Specialist: David C. Hilmers Mission Specialist: Richard M. Mullane Mission Specialist: Richard M. Mullane Mission Specialist: Richard M. Mullane Mission Specialist: Pierre J. Thuot Mission Specialist: Pierre J. Thuot Mission Specialist: Pierre J. Thuot Mission Duration: 96 hours (4 days), 10 hours, Mission Duration: 96 hours (4 days), 10 hours, Mission Duration: 96 hours (4 days), 10 hours, 18 minutes, 23 seconds 18 minutes, 23 seconds 18 minutes, 23 seconds Inclination: 62 degrees* Inclination: 62 degrees* Inclination: 62 degrees* Landing Speed at Touchdown: Approximately 199 Landing Speed at Touchdown: Approximately 199 Landing Speed at Touchdown: Approximately 199 knots (229 miles per hour) knots (229 miles per hour) knots (229 miles per hour) Landing Touchdown: Approximately 1,622 feet beyond Landing Touchdown: Approximately 1,622 feet beyond Landing Touchdown: Approximately 1,622 feet beyond threshold threshold threshold Landing Rollout: 7,900 feet Landing Rollout: 7,900 feet Landing Rollout: 7,900 feet Landed: Runway 23 dry lake bed at Edwards Air Force Landed: Runway 23 dry lake bed at Edwards Air Force Landed: Runway 23 dry lake bed at Edwards Air Force Base, California Base, California Base, California Payload: DOD Payload: DOD Payload: DOD *Record high (through 5/93) *Record high (through 5/93) *Record high (through 5/93)

STS-31 Mission Facts — Discovery — STS-31 Mission Facts — Discovery — STS-31 Mission Facts — Discovery — April 24–29, 1990 April 24–29, 1990 April 24–29, 1990

Commander: Loren J. Shriver Commander: Loren J. Shriver Commander: Loren J. Shriver Pilot: Charles F. Bolden Pilot: Charles F. Bolden Pilot: Charles F. Bolden Mission Specialist: Steven A. Hawley Mission Specialist: Steven A. Hawley Mission Specialist: Steven A. Hawley Mission Specialist: Bruce McCandless II Mission Specialist: Bruce McCandless II Mission Specialist: Bruce McCandless II Mission Specialist: Kathryn D. Sullivan Mission Specialist: Kathryn D. Sullivan Mission Specialist: Kathryn D. Sullivan Mission Duration: 120 hours (5 days), 1 hour, Mission Duration: 120 hours (5 days), 1 hour, Mission Duration: 120 hours (5 days), 1 hour, 16 minutes, 5 seconds 16 minutes, 5 seconds 16 minutes, 5 seconds Miles Traveled: 2,068,213 statute miles Miles Traveled: 2,068,213 statute miles Miles Traveled: 2,068,213 statute miles Inclination: 28.45 degrees Inclination: 28.45 degrees Inclination: 28.45 degrees Orbits of Earth: 76 Orbits of Earth: 76 Orbits of Earth: 76 Orbital Altitude: 311 by 331 nautical miles (357 by 380 Orbital Altitude: 311 by 331 nautical miles (357 by 380 Orbital Altitude: 311 by 331 nautical miles (357 by 380 statute miles), 331 by 332 nautical miles (380 by statute miles), 331 by 332 nautical miles (380 by statute miles), 331 by 332 nautical miles (380 by 382 statute miles), 330 by 334 nautical miles 382 statute miles), 330 by 334 nautical miles 382 statute miles), 330 by 334 nautical miles (379 by 384 statute miles) (379 by 384 statute miles) (379 by 384 statute miles) Landing Touchdown: Approximately 1,291 feet beyond Landing Touchdown: Approximately 1,291 feet beyond Landing Touchdown: Approximately 1,291 feet beyond threshold threshold threshold Landing Rollout: Approximately 8,874 feet Landing Rollout: Approximately 8,874 feet Landing Rollout: Approximately 8,874 feet Orbiter Weight at Landing: Approximately 189,118 Orbiter Weight at Landing: Approximately 189,118 Orbiter Weight at Landing: Approximately 189,118 pounds pounds pounds Lift-off Weight: Approximately 4,514,665 pounds Lift-off Weight: Approximately 4,514,665 pounds Lift-off Weight: Approximately 4,514,665 pounds Orbiter Weight at Lift-off: Approximately 249,109 Orbiter Weight at Lift-off: Approximately 249,109 Orbiter Weight at Lift-off: Approximately 249,109 pounds pounds pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 177 knots (203 miles per hour) mately 177 knots (203 miles per hour) mately 177 knots (203 miles per hour) Payload Weight Up: Approximately 28,673 pounds Payload Weight Up: Approximately 28,673 pounds Payload Weight Up: Approximately 28,673 pounds Payload Weight Down: Approximately 4,768 pounds Payload Weight Down: Approximately 4,768 pounds Payload Weight Down: Approximately 4,768 pounds Landed: Concrete runway 22 at Edwards Air Force Landed: Concrete runway 22 at Edwards Air Force Landed: Concrete runway 22 at Edwards Air Force Base, California Base, California Base, California

Y-26 Y-26 Y-26 STS-31 Mission Facts (Cont) STS-31 Mission Facts (Cont) STS-31 Mission Facts (Cont)

Payloads: Deployment of Hubble Space Telescope, Payloads: Deployment of Hubble Space Telescope, Payloads: Deployment of Hubble Space Telescope, IMAX camera in payload bay and in crew compart- IMAX camera in payload bay and in crew compart- IMAX camera in payload bay and in crew compart- ment, Protein Crystal Growth III-03, Investigation ment, Protein Crystal Growth III-03, Investigation ment, Protein Crystal Growth III-03, Investigation Into Polymer Membrane Processing-01, Air Force Into Polymer Membrane Processing-01, Air Force Into Polymer Membrane Processing-01, Air Force Maui Optical Site-05, Radiation Monitoring Equip- Maui Optical Site-05, Radiation Monitoring Equip- Maui Optical Site-05, Radiation Monitoring Equip- ment III-01, Student Experiment 82-16, and Ascent ment III-01, Student Experiment 82-16, and Ascent ment III-01, Student Experiment 82-16, and Ascent Particle Monitor 01 Particle Monitor 01 Particle Monitor 01

STS-41 Mission Facts — Discovery — STS-41 Mission Facts — Discovery — STS-41 Mission Facts — Discovery — October 6–10, 1990 October 6–10, 1990 October 6–10, 1990

Commander: Richard N. Richards Commander: Richard N. Richards Commander: Richard N. Richards Pilot: Robert D. Cabana Pilot: Robert D. Cabana Pilot: Robert D. Cabana Mission Specialist: Bruce E. Melnick Mission Specialist: Bruce E. Melnick Mission Specialist: Bruce E. Melnick Mission Specialist: William M. Shepherd Mission Specialist: William M. Shepherd Mission Specialist: William M. Shepherd Mission Specialist: Thomas D. Akers Mission Specialist: Thomas D. Akers Mission Specialist: Thomas D. Akers Mission Duration: 96 hours (4 days), 2 hours, Mission Duration: 96 hours (4 days), 2 hours, Mission Duration: 96 hours (4 days), 2 hours, 10 minutes 10 minutes 10 minutes Miles Traveled: 1,707,445 statute miles Miles Traveled: 1,707,445 statute miles Miles Traveled: 1,707,445 statute miles Inclination: 28.5 degrees Inclination: 28.5 degrees Inclination: 28.5 degrees Orbits of Earth: 65 Orbits of Earth: 65 Orbits of Earth: 65 Orbital Altitude: 160 by 160 nautical miles (184 by 184 Orbital Altitude: 160 by 160 nautical miles (184 by 184 Orbital Altitude: 160 by 160 nautical miles (184 by 184 statute miles), 177 by 160 nautical miles (203 by statute miles), 177 by 160 nautical miles (203 by statute miles), 177 by 160 nautical miles (203 by 184 statute miles), 160 by 156 nautical miles (184 184 statute miles), 160 by 156 nautical miles (184 184 statute miles), 160 by 156 nautical miles (184 by 179 statute miles), 157 by 156 nautical miles by 179 statute miles), 157 by 156 nautical miles by 179 statute miles), 157 by 156 nautical miles (180 by 179 statute miles) (180 by 179 statute miles) (180 by 179 statute miles) Landing Touchdown: Approximately 2,295 feet beyond Landing Touchdown: Approximately 2,295 feet beyond Landing Touchdown: Approximately 2,295 feet beyond threshold threshold threshold Landing Rollout: Approximately 8,532 feet Landing Rollout: Approximately 8,532 feet Landing Rollout: Approximately 8,532 feet Orbiter Weight at Landing: Approximately 197,986 Orbiter Weight at Landing: Approximately 197,986 Orbiter Weight at Landing: Approximately 197,986 pounds pounds pounds Lift-off Weight: Approximately 4,523,894 pounds Lift-off Weight: Approximately 4,523,894 pounds Lift-off Weight: Approximately 4,523,894 pounds Orbiter Weight at Lift-off: Approximately 293,019 Orbiter Weight at Lift-off: Approximately 293,019 Orbiter Weight at Lift-off: Approximately 293,019 pounds pounds pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 194 knots (223 miles per hour) mately 194 knots (223 miles per hour) mately 194 knots (223 miles per hour) Payload Weight Up: Approximately 48,812 pounds Payload Weight Up: Approximately 48,812 pounds Payload Weight Up: Approximately 48,812 pounds Payload Weight Down: Approximately 10,279 pounds Payload Weight Down: Approximately 10,279 pounds Payload Weight Down: Approximately 10,279 pounds Landed: Concrete runway 22 at Edwards Air Force Landed: Concrete runway 22 at Edwards Air Force Landed: Concrete runway 22 at Edwards Air Force Base, California Base, California Base, California Payloads: Deploy Ulysses, Shuttle Solar Backscatter Payloads: Deploy Ulysses, Shuttle Solar Backscatter Payloads: Deploy Ulysses, Shuttle Solar Backscatter Ultraviolet, Intelsat Solar Array Coupon, Solid-Sur- Ultraviolet, Intelsat Solar Array Coupon, Solid-Sur- Ultraviolet, Intelsat Solar Array Coupon, Solid-Sur- face Combustion Experiment, Investigations Into face Combustion Experiment, Investigations Into face Combustion Experiment, Investigations Into Polymer Membrane Processing, Chromosome Polymer Membrane Processing, Chromosome Polymer Membrane Processing, Chromosome and Plant Cell Division in Space, Physiological and Plant Cell Division in Space, Physiological and Plant Cell Division in Space, Physiological Systems Experiment, Voice Command System, Systems Experiment, Voice Command System, Systems Experiment, Voice Command System, Radiation Monitoring Equipment III, Air Force Maui Radiation Monitoring Equipment III, Air Force Maui Radiation Monitoring Equipment III, Air Force Maui Optical Site Optical Site Optical Site

Y-27 Y-27 Y-27 STS-38 Mission Facts — Atlantis — STS-38 Mission Facts — Atlantis — STS-38 Mission Facts — Atlantis — November 15–20, 1990 November 15–20, 1990 November 15–20, 1990 Commander: Richard O. Covey Commander: Richard O. Covey Commander: Richard O. Covey Pilot: Frank L. Culbertson Pilot: Frank L. Culbertson Pilot: Frank L. Culbertson Mission Specialist: Robert C. Springer Mission Specialist: Robert C. Springer Mission Specialist: Robert C. Springer Mission Specialist: Carl J. Meade Mission Specialist: Carl J. Meade Mission Specialist: Carl J. Meade Mission Specialist: Charles D. “Sam” Gemar Mission Specialist: Charles D. “Sam” Gemar Mission Specialist: Charles D. “Sam” Gemar Mission Duration: 96 hours (4 days), 21 hours, Mission Duration: 96 hours (4 days), 21 hours, Mission Duration: 96 hours (4 days), 21 hours, 55 minutes, 22 seconds 55 minutes, 22 seconds 55 minutes, 22 seconds Orbits of Earth: 79 Orbits of Earth: 79 Orbits of Earth: 79 Inclination: 28.5 degrees Inclination: 28.5 degrees Inclination: 28.5 degrees Landing Speed at Touchdown: Approximately Landing Speed at Touchdown: Approximately Landing Speed at Touchdown: Approximately 194 knots (223 miles per hour) 194 knots (223 miles per hour) 194 knots (223 miles per hour) Landing Touchdown: Approximately 1,414 feet beyond Landing Touchdown: Approximately 1,414 feet beyond Landing Touchdown: Approximately 1,414 feet beyond threshold threshold threshold Landing Rollout: Approximately 8,900 feet Landing Rollout: Approximately 8,900 feet Landing Rollout: Approximately 8,900 feet Landed: Runway 33 at Kennedy Space Center, Florida Landed: Runway 33 at Kennedy Space Center, Florida Landed: Runway 33 at Kennedy Space Center, Florida Payload: DOD Payload: DOD Payload: DOD

STS-35 Mission Facts — Columbia — STS-35 Mission Facts — Columbia — STS-35 Mission Facts — Columbia — December 2–10, 1990 December 2–10, 1990 December 2–10, 1990 Commander: Vance D. Brand Commander: Vance D. Brand Commander: Vance D. Brand Pilot: Guy S. Gardner Pilot: Guy S. Gardner Pilot: Guy S. Gardner Mission Specialist: Jeffrey A. Hoffman Mission Specialist: Jeffrey A. Hoffman Mission Specialist: Jeffrey A. Hoffman Mission Specialist: John M. Lounge Mission Specialist: John M. Lounge Mission Specialist: John M. Lounge Mission Specialist: Robert A.R. Parker Mission Specialist: Robert A.R. Parker Mission Specialist: Robert A.R. Parker Payload Specialist: Samuel T. Durrance Payload Specialist: Samuel T. Durrance Payload Specialist: Samuel T. Durrance Payload Specialist: Ronald A. Parise Payload Specialist: Ronald A. Parise Payload Specialist: Ronald A. Parise Mission Duration: 192 hours (8 days), 23 hours, Mission Duration: 192 hours (8 days), 23 hours, Mission Duration: 192 hours (8 days), 23 hours, 5 minutes, 8 seconds 5 minutes, 8 seconds 5 minutes, 8 seconds Miles Traveled: 3,728,636 statute miles Miles Traveled: 3,728,636 statute miles Miles Traveled: 3,728,636 statute miles Inclination: 28.45 degrees Inclination: 28.45 degrees Inclination: 28.45 degrees Orbits of Earth: 142 Orbits of Earth: 142 Orbits of Earth: 142 Orbital Altitude: 190 by 190 nautical miles (218 by 218 Orbital Altitude: 190 by 190 nautical miles (218 by 218 Orbital Altitude: 190 by 190 nautical miles (218 by 218 statute miles) statute miles) statute miles) Landing Touchdown: Approximately 2,000 feet beyond Landing Touchdown: Approximately 2,000 feet beyond Landing Touchdown: Approximately 2,000 feet beyond threshold threshold threshold Landing Rollout: Approximately 10,837 feet Landing Rollout: Approximately 10,837 feet Landing Rollout: Approximately 10,837 feet Orbiter Weight at Landing: Approximately 225,886 Orbiter Weight at Landing: Approximately 225,886 Orbiter Weight at Landing: Approximately 225,886 pounds pounds pounds Lift-off Weight: Approximately 4,523,199 pounds Lift-off Weight: Approximately 4,523,199 pounds Lift-off Weight: Approximately 4,523,199 pounds Orbiter Weight at Lift-off: Approximately 267,392 Orbiter Weight at Lift-off: Approximately 267,392 Orbiter Weight at Lift-off: Approximately 267,392 pounds pounds pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 202 knots (232 miles per hour) mately 202 knots (232 miles per hour) mately 202 knots (232 miles per hour) Payload Weight Up: Approximately 26,330 pounds Payload Weight Up: Approximately 26,330 pounds Payload Weight Up: Approximately 26,330 pounds Payload Weight Down: Approximately 26,330 pounds Payload Weight Down: Approximately 26,330 pounds Payload Weight Down: Approximately 26,330 pounds Landed: Concrete runway 22 at Edwards Air Force Landed: Concrete runway 22 at Edwards Air Force Landed: Concrete runway 22 at Edwards Air Force Base, California Base, California Base, California Payloads: Ultraviolet Astronomy TeIescope (Astro), Payloads: Ultraviolet Astronomy TeIescope (Astro), Payloads: Ultraviolet Astronomy TeIescope (Astro), Broad-Band X-Ray Telescope (BBXRT), Shuttle Broad-Band X-Ray Telescope (BBXRT), Shuttle Broad-Band X-Ray Telescope (BBXRT), Shuttle Amateur Radio Experiment (SAREX), Air Force Amateur Radio Experiment (SAREX), Air Force Amateur Radio Experiment (SAREX), Air Force Maui Optical Site (AMOS). Maui Optical Site (AMOS). Maui Optical Site (AMOS). Y-28 Y-28 Y-28 STS-37 Mission Facts — Atlantis — STS-37 Mission Facts — Atlantis — STS-37 Mission Facts — Atlantis — April 5–11, 1991 April 5–11, 1991 April 5–11, 1991

Commander: Steven R. Nagel Commander: Steven R. Nagel Commander: Steven R. Nagel Pilot: Kenneth D. Cameron Pilot: Kenneth D. Cameron Pilot: Kenneth D. Cameron Mission Specialist: Jerry L. Ross Mission Specialist: Jerry L. Ross Mission Specialist: Jerry L. Ross Mission Specialist: Jerome Apt Mission Specialist: Jerome Apt Mission Specialist: Jerome Apt Mission Specialist: Linda M. Godwin Mission Specialist: Linda M. Godwin Mission Specialist: Linda M. Godwin Mission Duration: 120 hours (5 days), 23 hours, Mission Duration: 120 hours (5 days), 23 hours, Mission Duration: 120 hours (5 days), 23 hours, 32 minutes, 44 seconds 32 minutes, 44 seconds 32 minutes, 44 seconds Miles Traveled: 2,456,263 statute miles Miles Traveled: 2,456,263 statute miles Miles Traveled: 2,456,263 statute miles Inclination: 28.45 degrees Inclination: 28.45 degrees Inclination: 28.45 degrees Orbits of Earth: 93 Orbits of Earth: 93 Orbits of Earth: 93 Orbital Altitude: 243 nautical miles (280 statute miles) Orbital Altitude: 243 nautical miles (280 statute miles) Orbital Altitude: 243 nautical miles (280 statute miles) circular orbit circular orbit circular orbit Landing Touchdown: Approximately 632 feet before Landing Touchdown: Approximately 632 feet before Landing Touchdown: Approximately 632 feet before threshold threshold threshold Landing Rollout: Approximately 6,600 feet Landing Rollout: Approximately 6,600 feet Landing Rollout: Approximately 6,600 feet Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately 191,050 pounds 191,050 pounds 191,050 pounds Lift-off Weight: Approximately 4,519,158 pounds Lift-off Weight: Approximately 4,519,158 pounds Lift-off Weight: Approximately 4,519,158 pounds Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately 254,971 pounds 254,971 pounds 254,971 pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 188 knots (216 miles per hour) mately 188 knots (216 miles per hour) mately 188 knots (216 miles per hour) Payload Weight Up: Approximately 36,621 pounds Payload Weight Up: Approximately 36,621 pounds Payload Weight Up: Approximately 36,621 pounds Payload Weight Down: Approximately 2,279 pounds Payload Weight Down: Approximately 2,279 pounds Payload Weight Down: Approximately 2,279 pounds Landed: Runway 33 dry lake bed at Edwards Air Force Landed: Runway 33 dry lake bed at Edwards Air Force Landed: Runway 33 dry lake bed at Edwards Air Force Base, California Base, California Base, California Payloads: Gamma-Ray Observatory (GRO), Crew/ Payloads: Gamma-Ray Observatory (GRO), Crew/ Payloads: Gamma-Ray Observatory (GRO), Crew/ Equipment Translation Aids (part of Extravehicular Equipment Translation Aids (part of Extravehicular Equipment Translation Aids (part of Extravehicular Activity Development Flight Experiment), Ascent Activity Development Flight Experiment), Ascent Activity Development Flight Experiment), Ascent Particle Monitor (APM), Bioserve Instrumenta- Particle Monitor (APM), Bioserve Instrumenta- Particle Monitor (APM), Bioserve Instrumenta- tion Technology Associates Materials Disper- tion Technology Associates Materials Disper- tion Technology Associates Materials Disper- sion Apparatus (BlMDA), Protein Crystal Growth sion Apparatus (BlMDA), Protein Crystal Growth sion Apparatus (BlMDA), Protein Crystal Growth (PCG)-Block Il, Space Station Heatpipe Advanced (PCG)-Block Il, Space Station Heatpipe Advanced (PCG)-Block Il, Space Station Heatpipe Advanced Radiator Element (SHARE)-ll, Shuttle Amateur Radiator Element (SHARE)-ll, Shuttle Amateur Radiator Element (SHARE)-ll, Shuttle Amateur Radio Experiment (SAREX)-ll, Radiation Monitor- Radio Experiment (SAREX)-ll, Radiation Monitor- Radio Experiment (SAREX)-ll, Radiation Monitor- ing Equipment (RME)-lIl, Air Force Maui Optical ing Equipment (RME)-lIl, Air Force Maui Optical ing Equipment (RME)-lIl, Air Force Maui Optical Site (AMOS) Calibration Test Site (AMOS) Calibration Test Site (AMOS) Calibration Test Extravehicular Activity (EVA): Jerry L. Ross and Extravehicular Activity (EVA): Jerry L. Ross and Extravehicular Activity (EVA): Jerry L. Ross and Jerome Apt: EVA No. 1 duration, 4 hours, 38 Jerome Apt: EVA No. 1 duration, 4 hours, 38 Jerome Apt: EVA No. 1 duration, 4 hours, 38 minutes; EVA No. 2 duration, 6 hours, 11 minutes. minutes; EVA No. 2 duration, 6 hours, 11 minutes. minutes; EVA No. 2 duration, 6 hours, 11 minutes. EVA No. 1 was an unscheduled EVA to manually EVA No. 1 was an unscheduled EVA to manually EVA No. 1 was an unscheduled EVA to manually deploy the Gamma-Ray Observatory’s high-gain deploy the Gamma-Ray Observatory’s high-gain deploy the Gamma-Ray Observatory’s high-gain antenna, which failed to deploy upon ground antenna, which failed to deploy upon ground antenna, which failed to deploy upon ground command. Following the successful deploy of the command. Following the successful deploy of the command. Following the successful deploy of the antenna, the astronauts spent the remainder of the antenna, the astronauts spent the remainder of the antenna, the astronauts spent the remainder of the EVA on Extravehicular Activity Development Flight EVA on Extravehicular Activity Development Flight EVA on Extravehicular Activity Development Flight Experiment activities. Experiment activities. Experiment activities.

Y-29 Y-29 Y-29 STS-39 Mission Facts — Discovery — STS-39 Mission Facts — Discovery — STS-39 Mission Facts — Discovery — April 28–May 6, 1991 April 28–May 6, 1991 April 28–May 6, 1991

Commander: Michael L. Coats Commander: Michael L. Coats Commander: Michael L. Coats Pilot: L. Blaine Hammond, Jr. Pilot: L. Blaine Hammond, Jr. Pilot: L. Blaine Hammond, Jr. Mission Specialist: Gregory J. Harbaugh Mission Specialist: Gregory J. Harbaugh Mission Specialist: Gregory J. Harbaugh Mission Specialist: Donald R. McMonagle Mission Specialist: Donald R. McMonagle Mission Specialist: Donald R. McMonagle Mission Specialist: Guion S. Bluford, Jr. Mission Specialist: Guion S. Bluford, Jr. Mission Specialist: Guion S. Bluford, Jr. Mission Specialist: Charles L. (Lacy) Veach Mission Specialist: Charles L. (Lacy) Veach Mission Specialist: Charles L. (Lacy) Veach Mission Specialist: Richard J. Hieb Mission Specialist: Richard J. Hieb Mission Specialist: Richard J. Hieb Mission Duration: 192 hours (8 days), 7 hours, Mission Duration: 192 hours (8 days), 7 hours, Mission Duration: 192 hours (8 days), 7 hours, 22 minutes, 22 seconds 22 minutes, 22 seconds 22 minutes, 22 seconds Miles Traveled: Approximately 3.47 million statute miles Miles Traveled: Approximately 3.47 million statute miles Miles Traveled: Approximately 3.47 million statute miles Inclination: 57 degrees Inclination: 57 degrees Inclination: 57 degrees Orbits of Earth: 134 Orbits of Earth: 134 Orbits of Earth: 134 Orbital Altitude: 140 nautical miles (161 statute miles) Orbital Altitude: 140 nautical miles (161 statute miles) Orbital Altitude: 140 nautical miles (161 statute miles) circular orbit circular orbit circular orbit Landing Touchdown: Approximately 168 feet beyond Landing Touchdown: Approximately 168 feet beyond Landing Touchdown: Approximately 168 feet beyond threshold threshold threshold Landing Rollout: Approximately 9,152 feet Landing Rollout: Approximately 9,152 feet Landing Rollout: Approximately 9,152 feet Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately 210,811 pounds 210,811 pounds 210,811 pounds Lift-off Weight: Approximately 4,512,698 pounds Lift-off Weight: Approximately 4,512,698 pounds Lift-off Weight: Approximately 4,512,698 pounds Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately 246,986 pounds 246,986 pounds 246,986 pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 210 knots (242 miles per hour) mately 210 knots (242 miles per hour) mately 210 knots (242 miles per hour) Payload Weight Up: Approximately 21,413 pounds Payload Weight Up: Approximately 21,413 pounds Payload Weight Up: Approximately 21,413 pounds Payload Weight Down: Approximately 20,586 pounds Payload Weight Down: Approximately 20,586 pounds Payload Weight Down: Approximately 20,586 pounds Landed: Runway 15 at Kennedy Space Center, Florida Landed: Runway 15 at Kennedy Space Center, Florida Landed: Runway 15 at Kennedy Space Center, Florida Payloads: Infrared Background Signature Survey (lBSS), Payloads: Infrared Background Signature Survey (lBSS), Payloads: Infrared Background Signature Survey (lBSS), Air Force Program (AFP)-675, Space Test Payload Air Force Program (AFP)-675, Space Test Payload Air Force Program (AFP)-675, Space Test Payload (STP)-I, Multi-Purpose Experiment Canister (STP)-I, Multi-Purpose Experiment Canister (STP)-I, Multi-Purpose Experiment Canister (MPEC), Cloud Logic to Optimize Use of Defense (MPEC), Cloud Logic to Optimize Use of Defense (MPEC), Cloud Logic to Optimize Use of Defense Systems (CLOUDS)-1A, Radiation Monitoring Systems (CLOUDS)-1A, Radiation Monitoring Systems (CLOUDS)-1A, Radiation Monitoring Equipment (RME)-lll Equipment (RME)-lll Equipment (RME)-lll

STS-40 Mission Facts — Columbia — STS-40 Mission Facts — Columbia — STS-40 Mission Facts — Columbia — June 5–14, 1991 June 5–14, 1991 June 5–14, 1991

Commander: Bryan D. O’Conner Commander: Bryan D. O’Conner Commander: Bryan D. O’Conner Pilot: Sidney M. Gutierrez Pilot: Sidney M. Gutierrez Pilot: Sidney M. Gutierrez Mission Specialist: M. Rhea Seddon Mission Specialist: M. Rhea Seddon Mission Specialist: M. Rhea Seddon Mission Specialist: James P. Bagian Mission Specialist: James P. Bagian Mission Specialist: James P. Bagian Mission Specialist: Tamara E. Jernigan Mission Specialist: Tamara E. Jernigan Mission Specialist: Tamara E. Jernigan Payload Specialist: F. Drew Gaffney Payload Specialist: F. Drew Gaffney Payload Specialist: F. Drew Gaffney Payload Specialist: Millie Hughes-Fulford Payload Specialist: Millie Hughes-Fulford Payload Specialist: Millie Hughes-Fulford Mission Duration: 216 hours (9 days), 2 hours, Mission Duration: 216 hours (9 days), 2 hours, Mission Duration: 216 hours (9 days), 2 hours, 14 minutes, 20 seconds 14 minutes, 20 seconds 14 minutes, 20 seconds Miles Traveled: Approximately 3,779,940 statute miles Miles Traveled: Approximately 3,779,940 statute miles Miles Traveled: Approximately 3,779,940 statute miles Inclination: 39 degrees Inclination: 39 degrees Inclination: 39 degrees

Y-30 Y-30 Y-30 STS-40 Mission Facts (Cont) STS-40 Mission Facts (Cont) STS-40 Mission Facts (Cont)

Orbits of Earth: 146 Orbits of Earth: 146 Orbits of Earth: 146 Orbital Altitude: 160 by 150 nautical miles (184 by Orbital Altitude: 160 by 150 nautical miles (184 by Orbital Altitude: 160 by 150 nautical miles (184 by 172 statute miles) 172 statute miles) 172 statute miles) Landing Touchdown: Approximately 1,485 feet beyond Landing Touchdown: Approximately 1,485 feet beyond Landing Touchdown: Approximately 1,485 feet beyond threshold threshold threshold Landing Rollout: Approximately 9,438 feet Landing Rollout: Approximately 9,438 feet Landing Rollout: Approximately 9,438 feet Orbiter Weight at Landing: Approximately 226,534 Orbiter Weight at Landing: Approximately 226,534 Orbiter Weight at Landing: Approximately 226,534 pounds pounds pounds Lift-off Weight: Approximately 4,519,081 pounds Lift-off Weight: Approximately 4,519,081 pounds Lift-off Weight: Approximately 4,519,081 pounds Orbiter Weight at Lift-off: Approximately 250,398 Orbiter Weight at Lift-off: Approximately 250,398 Orbiter Weight at Lift-off: Approximately 250,398 pounds pounds pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 200 knots (230 miles per hour) mately 200 knots (230 miles per hour) mately 200 knots (230 miles per hour) Payload Weight Up: Approximately 25,942 pounds Payload Weight Up: Approximately 25,942 pounds Payload Weight Up: Approximately 25,942 pounds Payload Weight Down: Approximately 25,942 pounds Payload Weight Down: Approximately 25,942 pounds Payload Weight Down: Approximately 25,942 pounds Landed: Concrete runway 22 at Edwards AFB, California Landed: Concrete runway 22 at Edwards AFB, California Landed: Concrete runway 22 at Edwards AFB, California Payloads: Spacelab Life Sciences (SLS)-1 with long Payloads: Spacelab Life Sciences (SLS)-1 with long Payloads: Spacelab Life Sciences (SLS)-1 with long module, getaway special bridge assembly with module, getaway special bridge assembly with module, getaway special bridge assembly with 12 getaway specials, Physiological Monitoring 12 getaway specials, Physiological Monitoring 12 getaway specials, Physiological Monitoring System (PMS), Urine Monitoring System (UMS), System (PMS), Urine Monitoring System (UMS), System (PMS), Urine Monitoring System (UMS), Animal Enclosure Modules (AEM), Middeck Zero- Animal Enclosure Modules (AEM), Middeck Zero- Animal Enclosure Modules (AEM), Middeck Zero- gravity Dynamics Experiment (MODE), 7 Orbiter gravity Dynamics Experiment (MODE), 7 Orbiter gravity Dynamics Experiment (MODE), 7 Orbiter Experiments Program experiments Experiments Program experiments Experiments Program experiments

STS-43 Mission Facts — Atlantis — STS-43 Mission Facts — Atlantis — STS-43 Mission Facts — Atlantis — August 2–11, 1991 August 2–11, 1991 August 2–11, 1991

Commander: John E. Blaha Commander: John E. Blaha Commander: John E. Blaha Pilot: Michael A. Baker Pilot: Michael A. Baker Pilot: Michael A. Baker Mission Specialist: Shannon W. Lucid Mission Specialist: Shannon W. Lucid Mission Specialist: Shannon W. Lucid Mission Specialist: G. David Low Mission Specialist: G. David Low Mission Specialist: G. David Low Mission Specialist: James C. Adamson Mission Specialist: James C. Adamson Mission Specialist: James C. Adamson Mission Duration: 192 hours (8 days), 21 hours, Mission Duration: 192 hours (8 days), 21 hours, Mission Duration: 192 hours (8 days), 21 hours, 21 minutes, 25 seconds 21 minutes, 25 seconds 21 minutes, 25 seconds Miles Traveled: Approximately 3,700,400 statute miles Miles Traveled: Approximately 3,700,400 statute miles Miles Traveled: Approximately 3,700,400 statute miles Inclination: 28.45 degrees Inclination: 28.45 degrees Inclination: 28.45 degrees Orbits of Earth: 142 Orbits of Earth: 142 Orbits of Earth: 142 Orbital Altitude: 160 nautical miles (184 statute miles) Orbital Altitude: 160 nautical miles (184 statute miles) Orbital Altitude: 160 nautical miles (184 statute miles) circular orbit circular orbit circular orbit Landing Touchdown: Approximately 1,986 feet beyond Landing Touchdown: Approximately 1,986 feet beyond Landing Touchdown: Approximately 1,986 feet beyond threshold threshold threshold Landing Rollout: Approximately 9,890 feet Landing Rollout: Approximately 9,890 feet Landing Rollout: Approximately 9,890 feet Orbiter Weight at Landing: Approximately 196,735 Orbiter Weight at Landing: Approximately 196,735 Orbiter Weight at Landing: Approximately 196,735 pounds pounds pounds Lift-off Weight: Approximately 4,526,488 pounds Lift-off Weight: Approximately 4,526,488 pounds Lift-off Weight: Approximately 4,526,488 pounds Orbiter Weight at Lift-off: Approximately 259,382 Orbiter Weight at Lift-off: Approximately 259,382 Orbiter Weight at Lift-off: Approximately 259,382 pounds pounds pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 203 knots (233 miles per hour) mately 203 knots (233 miles per hour) mately 203 knots (233 miles per hour) Payload Weight Up: Approximately 46,882 pounds Payload Weight Up: Approximately 46,882 pounds Payload Weight Up: Approximately 46,882 pounds Payload Weight Down: Approximately 9,242 pounds Payload Weight Down: Approximately 9,242 pounds Payload Weight Down: Approximately 9,242 pounds

Y-31 Y-31 Y-31 STS-43 Mission Facts (Cont) STS-43 Mission Facts (Cont) STS-43 Mission Facts (Cont)

Landed: Runway 15 at Kennedy Space Center, Florida Landed: Runway 15 at Kennedy Space Center, Florida Landed: Runway 15 at Kennedy Space Center, Florida Payloads: Tracking and Data Relay Satellite Payloads: Tracking and Data Relay Satellite Payloads: Tracking and Data Relay Satellite (TDRS)-E/lnertial Upper Stage (lUS), Space (TDRS)-E/lnertial Upper Stage (lUS), Space (TDRS)-E/lnertial Upper Stage (lUS), Space Station Heatpipe Advanced Radiator Element Station Heatpipe Advanced Radiator Element Station Heatpipe Advanced Radiator Element (SHARE)-ll, Shuttle Solar Backscatter Ultraviolet (SHARE)-ll, Shuttle Solar Backscatter Ultraviolet (SHARE)-ll, Shuttle Solar Backscatter Ultraviolet (SSBUV) instrument 03, Optical Communications (SSBUV) instrument 03, Optical Communications (SSBUV) instrument 03, Optical Communications Through the Shuttle Window (OCTW), Air Force Through the Shuttle Window (OCTW), Air Force Through the Shuttle Window (OCTW), Air Force Maui Optical Site (AMOS) Calibration Test, Auroral Maui Optical Site (AMOS) Calibration Test, Auroral Maui Optical Site (AMOS) Calibration Test, Auroral Photography Experiment (APE)-B, Bioserve-ln- Photography Experiment (APE)-B, Bioserve-ln- Photography Experiment (APE)-B, Bioserve-ln- strumentation Technology Associates Materials strumentation Technology Associates Materials strumentation Technology Associates Materials Dispersion Apparatus Dispersion Apparatus Dispersion Apparatus (BlMDA)-02, Investigations Into Polymer Mem- (BlMDA)-02, Investigations Into Polymer Mem- (BlMDA)-02, Investigations Into Polymer Mem- brane Processing (IPMP)-03, Protein Crystal brane Processing (IPMP)-03, Protein Crystal brane Processing (IPMP)-03, Protein Crystal Growth Ill Block Il, Space Acceleration Measure- Growth Ill Block Il, Space Acceleration Measure- Growth Ill Block Il, Space Acceleration Measure- ment System (SAMS), Solid Surface Combustion ment System (SAMS), Solid Surface Combustion ment System (SAMS), Solid Surface Combustion Experiment (SSCE)-02, Tank Pressure Control Experiment (SSCE)-02, Tank Pressure Control Experiment (SSCE)-02, Tank Pressure Control Experiment (TPCE) Experiment (TPCE) Experiment (TPCE)

STS-48 Mission Facts — Discovery — STS-48 Mission Facts — Discovery — STS-48 Mission Facts — Discovery — September 12–18, 1991 September 12–18, 1991 September 12–18, 1991

Commander: John O. Creighton Commander: John O. Creighton Commander: John O. Creighton Pilot: Kenneth S. Reightler, Jr. Pilot: Kenneth S. Reightler, Jr. Pilot: Kenneth S. Reightler, Jr. Mission Specialist: James F. BuchIi Mission Specialist: James F. BuchIi Mission Specialist: James F. BuchIi Mission Specialist: Mark N. Brown Mission Specialist: Mark N. Brown Mission Specialist: Mark N. Brown Mission Specialist: Charles D. “Sam” Gemar Mission Specialist: Charles D. “Sam” Gemar Mission Specialist: Charles D. “Sam” Gemar Mission Duration: 120 hours (5 days), 8 hours, Mission Duration: 120 hours (5 days), 8 hours, Mission Duration: 120 hours (5 days), 8 hours, 27 minutes, 34 seconds 27 minutes, 34 seconds 27 minutes, 34 seconds Miles Traveled: Approximately 2,193,670 statute miles Miles Traveled: Approximately 2,193,670 statute miles Miles Traveled: Approximately 2,193,670 statute miles Inclination: 57 degrees Inclination: 57 degrees Inclination: 57 degrees Orbits of Earth: 81 Orbits of Earth: 81 Orbits of Earth: 81 Orbital Altitude: 308 nautical miles (355 statute miles) Orbital Altitude: 308 nautical miles (355 statute miles) Orbital Altitude: 308 nautical miles (355 statute miles) circular orbit circular orbit circular orbit Landing Touchdown: Approximately 1,829 feet beyond Landing Touchdown: Approximately 1,829 feet beyond Landing Touchdown: Approximately 1,829 feet beyond threshold threshold threshold Landing Rollout: Approximately 8,790 feet Landing Rollout: Approximately 8,790 feet Landing Rollout: Approximately 8,790 feet Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately 192,507 pounds 192,507 pounds 192,507 pounds Lift-off Weight: Approximately 4,507,348 pounds Lift-off Weight: Approximately 4,507,348 pounds Lift-off Weight: Approximately 4,507,348 pounds Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately 239,735 pounds 239,735 pounds 239,735 pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 216 knots (249 miles per hour) mately 216 knots (249 miles per hour) mately 216 knots (249 miles per hour) Payload Weight Up: Approximately 17,317 pounds Payload Weight Up: Approximately 17,317 pounds Payload Weight Up: Approximately 17,317 pounds Payload Weight Down: Approximately 2,898 pounds Payload Weight Down: Approximately 2,898 pounds Payload Weight Down: Approximately 2,898 pounds Landed: Concrete runway 22 at Edwards Air Force Landed: Concrete runway 22 at Edwards Air Force Landed: Concrete runway 22 at Edwards Air Force Base, California Base, California Base, California Payloads: Upper Atmosphere Research Satellite Payloads: Upper Atmosphere Research Satellite Payloads: Upper Atmosphere Research Satellite (UARS), Ascent Particle Monitor (APM)-03, (UARS), Ascent Particle Monitor (APM)-03, (UARS), Ascent Particle Monitor (APM)-03, Physiological and Anatomical Rodent Experiment Physiological and Anatomical Rodent Experiment Physiological and Anatomical Rodent Experiment (PARE)-01, Protein Crystal Growth (PARE)-01, Protein Crystal Growth (PARE)-01, Protein Crystal Growth (PCG)-ll-2, Middeck Zero-Gravity Dynamics (PCG)-ll-2, Middeck Zero-Gravity Dynamics (PCG)-ll-2, Middeck Zero-Gravity Dynamics

Y-32 Y-32 Y-32 STS-48 Mission Facts (Cont) STS-48 Mission Facts (Cont) STS-48 Mission Facts (Cont)

Experiment (MODE)-01, Investigations Into Poly- Experiment (MODE)-01, Investigations Into Poly- Experiment (MODE)-01, Investigations Into Poly- mer Membrane Processing (IPMP)-04, Cosmic mer Membrane Processing (IPMP)-04, Cosmic mer Membrane Processing (IPMP)-04, Cosmic Radiation Effects and Activation Monitor (CREAM- Radiation Effects and Activation Monitor (CREAM- Radiation Effects and Activation Monitor (CREAM- 02), Radiation Monitoring Equipment (RME)-lll-06, 02), Radiation Monitoring Equipment (RME)-lll-06, 02), Radiation Monitoring Equipment (RME)-lll-06, Shuttle Activation Monitor (SAM)-03, Air Force Shuttle Activation Monitor (SAM)-03, Air Force Shuttle Activation Monitor (SAM)-03, Air Force Maui Optical Site (AMOS) Calibration Test Maui Optical Site (AMOS) Calibration Test Maui Optical Site (AMOS) Calibration Test

STS-44 Mission Facts — Atlantis — STS-44 Mission Facts — Atlantis — STS-44 Mission Facts — Atlantis — November 24–December 1, 1991 November 24–December 1, 1991 November 24–December 1, 1991

Commander: Frederick D. Gregory Commander: Frederick D. Gregory Commander: Frederick D. Gregory Pilot: Terrence T. Henricks Pilot: Terrence T. Henricks Pilot: Terrence T. Henricks Mission Specialist: F. Story Musgrave Mission Specialist: F. Story Musgrave Mission Specialist: F. Story Musgrave Mission Specialist: Mario Runco, Jr. Mission Specialist: Mario Runco, Jr. Mission Specialist: Mario Runco, Jr. Mission Specialist: James S. Voss Mission Specialist: James S. Voss Mission Specialist: James S. Voss Payload Specialist: Thomas J. Hennen Payload Specialist: Thomas J. Hennen Payload Specialist: Thomas J. Hennen Mission Duration: 144 hours (6 days), 22 hours, 50 Mission Duration: 144 hours (6 days), 22 hours, 50 Mission Duration: 144 hours (6 days), 22 hours, 50 minutes, 42 seconds minutes, 42 seconds minutes, 42 seconds Miles Traveled: Approximately 2,890,067 statute miles Miles Traveled: Approximately 2,890,067 statute miles Miles Traveled: Approximately 2,890,067 statute miles Inclination: 28.45 degrees Inclination: 28.45 degrees Inclination: 28.45 degrees Orbits of Earth: 109 Orbits of Earth: 109 Orbits of Earth: 109 Orbital Altitude: 195 nautical miles (225 statute miles) Orbital Altitude: 195 nautical miles (225 statute miles) Orbital Altitude: 195 nautical miles (225 statute miles) circular orbit circular orbit circular orbit Landing Touchdown: Approximately 2,607 feet beyond Landing Touchdown: Approximately 2,607 feet beyond Landing Touchdown: Approximately 2,607 feet beyond threshold threshold threshold Landing Rollout: Approximately 11,191 feet Landing Rollout: Approximately 11,191 feet Landing Rollout: Approximately 11,191 feet Orbiter Weight at Landing: Approximately 193,825 Orbiter Weight at Landing: Approximately 193,825 Orbiter Weight at Landing: Approximately 193,825 pounds pounds pounds Lift-off Weight: Approximately 4,526,272 pounds Lift-off Weight: Approximately 4,526,272 pounds Lift-off Weight: Approximately 4,526,272 pounds Orbiter Weight at Lift-off: Approximately 259,629 Orbiter Weight at Lift-off: Approximately 259,629 Orbiter Weight at Lift-off: Approximately 259,629 pounds pounds pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 183 knots (210 miles per hour) mately 183 knots (210 miles per hour) mately 183 knots (210 miles per hour) Payload Weight Up: Approximately 44,628 pounds Payload Weight Up: Approximately 44,628 pounds Payload Weight Up: Approximately 44,628 pounds Payload Weight Down: Approximately 7,010 pounds Payload Weight Down: Approximately 7,010 pounds Payload Weight Down: Approximately 7,010 pounds Landed: Runway 05 dry lake bed at Edwards Air Force Landed: Runway 05 dry lake bed at Edwards Air Force Landed: Runway 05 dry lake bed at Edwards Air Force Base, California Base, California Base, California Payloads: Defense Support Program satellite/ Payloads: Defense Support Program satellite/ Payloads: Defense Support Program satellite/ Inertial Upper Stage, Interim Operational Contami- Inertial Upper Stage, Interim Operational Contami- Inertial Upper Stage, Interim Operational Contami- nation Monitor, Terra Scout, Military Man in Space, nation Monitor, Terra Scout, Military Man in Space, nation Monitor, Terra Scout, Military Man in Space, Shuttle Activation Monitor, Cosmic Radiation Ef- Shuttle Activation Monitor, Cosmic Radiation Ef- Shuttle Activation Monitor, Cosmic Radiation Ef- fects and Activation Monitor, Radiation Monitoring fects and Activation Monitor, Radiation Monitoring fects and Activation Monitor, Radiation Monitoring Equipment Ill, Air Force Maui Optical Site Calibra- Equipment Ill, Air Force Maui Optical Site Calibra- Equipment Ill, Air Force Maui Optical Site Calibra- tion Test, Ultraviolet Plume Instrument, Visual tion Test, Ultraviolet Plume Instrument, Visual tion Test, Ultraviolet Plume Instrument, Visual Function Tester 1 Function Tester 1 Function Tester 1

STS-42 Mission Facts — Discovery — STS-42 Mission Facts — Discovery — STS-42 Mission Facts — Discovery — January 22–30, 1992 January 22–30, 1992 January 22–30, 1992

Commander: Ronald J. Grabe Commander: Ronald J. Grabe Commander: Ronald J. Grabe Pilot: Stephen S. Oswald Pilot: Stephen S. Oswald Pilot: Stephen S. Oswald Mission Specialist: David C. Hilmers Mission Specialist: David C. Hilmers Mission Specialist: David C. Hilmers

Y-33 Y-33 Y-33 STS-42 Mission Facts (Cont) STS-42 Mission Facts (Cont) STS-42 Mission Facts (Cont)

Mission Specialist: Norman E. Thagard Mission Specialist: Norman E. Thagard Mission Specialist: Norman E. Thagard Mission Specialist: William F. Readdy Mission Specialist: William F. Readdy Mission Specialist: William F. Readdy Payload Specialist: Ulf D. Merbold Payload Specialist: Ulf D. Merbold Payload Specialist: Ulf D. Merbold Payload Specialist: Roberta L. Bondar Payload Specialist: Roberta L. Bondar Payload Specialist: Roberta L. Bondar Mission Duration: 192 hours (8 days), 1 hour, 14 min- Mission Duration: 192 hours (8 days), 1 hour, 14 min- Mission Duration: 192 hours (8 days), 1 hour, 14 min- utes, 45 seconds utes, 45 seconds utes, 45 seconds Miles Traveled: Approximately 3,359,830 statute miles Miles Traveled: Approximately 3,359,830 statute miles Miles Traveled: Approximately 3,359,830 statute miles Inclination: 57 degrees Inclination: 57 degrees Inclination: 57 degrees Orbits of Earth: 129 Orbits of Earth: 129 Orbits of Earth: 129 Orbital Altitude: 163 nautical miles (188 statute miles) Orbital Altitude: 163 nautical miles (188 statute miles) Orbital Altitude: 163 nautical miles (188 statute miles) circular orbit circular orbit circular orbit Landing Touchdown: Approximately 2,835 feet beyond Landing Touchdown: Approximately 2,835 feet beyond Landing Touchdown: Approximately 2,835 feet beyond threshold threshold threshold Landing Rollout: Approximately 9,811 feet Landing Rollout: Approximately 9,811 feet Landing Rollout: Approximately 9,811 feet Orbiter Weight at Landing: Approximately 218,016 Orbiter Weight at Landing: Approximately 218,016 Orbiter Weight at Landing: Approximately 218,016 pounds pounds pounds Lift-off Weight: Approximately 4,507,474 pounds Lift-off Weight: Approximately 4,507,474 pounds Lift-off Weight: Approximately 4,507,474 pounds Orbiter Weight at Lift-off: Approximately 243,395 Orbiter Weight at Lift-off: Approximately 243,395 Orbiter Weight at Lift-off: Approximately 243,395 pounds pounds pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 199 knots (229 miles per hour) mately 199 knots (229 miles per hour) mately 199 knots (229 miles per hour) Payload Weight Up: Approximately 28,663 pounds Payload Weight Up: Approximately 28,663 pounds Payload Weight Up: Approximately 28,663 pounds Payload Weight Down: Approximately 28,663 pounds Payload Weight Down: Approximately 28,663 pounds Payload Weight Down: Approximately 28,663 pounds Landed: Concrete runway 22 at Edwards Air Force Landed: Concrete runway 22 at Edwards Air Force Landed: Concrete runway 22 at Edwards Air Force Base, California Base, California Base, California Payloads: International Microgravity Laboratory Payloads: International Microgravity Laboratory Payloads: International Microgravity Laboratory (lML)-1, getaway special (GAS) bridge with 10 (lML)-1, getaway special (GAS) bridge with 10 (lML)-1, getaway special (GAS) bridge with 10 getaway specials, IMAX camera, Gelation of Sols: getaway specials, IMAX camera, Gelation of Sols: getaway specials, IMAX camera, Gelation of Sols: Applied Microgravity Research Applied Microgravity Research Applied Microgravity Research (GOSAMR)-1, Investigations Into Polymer Mem- (GOSAMR)-1, Investigations Into Polymer Mem- (GOSAMR)-1, Investigations Into Polymer Mem- brane Processing (IPMP), Radiation Monitoring brane Processing (IPMP), Radiation Monitoring brane Processing (IPMP), Radiation Monitoring Equipment (RME)-lll, Student Experiment 81-09: Equipment (RME)-lll, Student Experiment 81-09: Equipment (RME)-lll, Student Experiment 81-09: Convection in Zero Gravity, Student Experiment Convection in Zero Gravity, Student Experiment Convection in Zero Gravity, Student Experiment 83-02: Capillary Rise of Liquid Through Granular 83-02: Capillary Rise of Liquid Through Granular 83-02: Capillary Rise of Liquid Through Granular Porous Media Porous Media Porous Media

STS-45 Mission Facts — Atlantis — STS-45 Mission Facts — Atlantis — STS-45 Mission Facts — Atlantis — March 24–April 2, 1992 March 24–April 2, 1992 March 24–April 2, 1992

Commander: Charles F. Bolden Commander: Charles F. Bolden Commander: Charles F. Bolden Pilot: Brian Duffy Pilot: Brian Duffy Pilot: Brian Duffy Payload Commander: Kathryn D. Sullivan Payload Commander: Kathryn D. Sullivan Payload Commander: Kathryn D. Sullivan Mission Specialist: David C. Leestma Mission Specialist: David C. Leestma Mission Specialist: David C. Leestma Mission Specialist: C. Michael Foale Mission Specialist: C. Michael Foale Mission Specialist: C. Michael Foale Payload Specialist: Dirk D. Frimout Payload Specialist: Dirk D. Frimout Payload Specialist: Dirk D. Frimout Payload Specialist: Byron K. Lichtenberg Payload Specialist: Byron K. Lichtenberg Payload Specialist: Byron K. Lichtenberg Mission Duration: 192 hours (8 days), 22 hours, Mission Duration: 192 hours (8 days), 22 hours, Mission Duration: 192 hours (8 days), 22 hours, 9 minutes, 25 seconds 9 minutes, 25 seconds 9 minutes, 25 seconds Miles Traveled: Approximately 3,724,946 statute miles Miles Traveled: Approximately 3,724,946 statute miles Miles Traveled: Approximately 3,724,946 statute miles

Y-34 Y-34 Y-34 STS-45 Mission Facts (Cont) STS-45 Mission Facts (Cont) STS-45 Mission Facts (Cont)

Inclination: 57 degrees Inclination: 57 degrees Inclination: 57 degrees Orbits of Earth: 143 Orbits of Earth: 143 Orbits of Earth: 143 Orbital Altitude: 160 nautical miles (184 statute miles) Orbital Altitude: 160 nautical miles (184 statute miles) Orbital Altitude: 160 nautical miles (184 statute miles) circular orbit circular orbit circular orbit Landing Touchdown: Approximately 1,800 feet beyond Landing Touchdown: Approximately 1,800 feet beyond Landing Touchdown: Approximately 1,800 feet beyond threshold threshold threshold Landing Rollout: Approximately 9,217 feet Landing Rollout: Approximately 9,217 feet Landing Rollout: Approximately 9,217 feet Orbiter Weight at Landing: Approximately 205,042 Orbiter Weight at Landing: Approximately 205,042 Orbiter Weight at Landing: Approximately 205,042 pounds pounds pounds Lift-off Weight: Approximately 4,496,035 pounds Lift-off Weight: Approximately 4,496,035 pounds Lift-off Weight: Approximately 4,496,035 pounds Orbiter Weight at Lift-off: Approximately 233,650 Orbiter Weight at Lift-off: Approximately 233,650 Orbiter Weight at Lift-off: Approximately 233,650 pounds pounds pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 195 knots (224 miles per hour) mately 195 knots (224 miles per hour) mately 195 knots (224 miles per hour) Payload Weight Up: Approximately 17,683 pounds Payload Weight Up: Approximately 17,683 pounds Payload Weight Up: Approximately 17,683 pounds Payload Weight Down: Approximately 17,683 pounds Payload Weight Down: Approximately 17,683 pounds Payload Weight Down: Approximately 17,683 pounds Landed: Concrete runway 33 at Kennedy Space Landed: Concrete runway 33 at Kennedy Space Landed: Concrete runway 33 at Kennedy Space Center, Florida Center, Florida Center, Florida Payloads: Atmospheric Laboratory for Applications Payloads: Atmospheric Laboratory for Applications Payloads: Atmospheric Laboratory for Applications and Science (ATLAS)-1, Shuttle Solar Backscatter and Science (ATLAS)-1, Shuttle Solar Backscatter and Science (ATLAS)-1, Shuttle Solar Backscatter Ultraviolet (SSBUV)-4, Getaway Special Experi- Ultraviolet (SSBUV)-4, Getaway Special Experi- Ultraviolet (SSBUV)-4, Getaway Special Experi- ment G-229, Space Tissue Loss (STL)-1, Radiation ment G-229, Space Tissue Loss (STL)-1, Radiation ment G-229, Space Tissue Loss (STL)-1, Radiation Monitoring Equipment (RME)-lIl, Visual Function Monitoring Equipment (RME)-lIl, Visual Function Monitoring Equipment (RME)-lIl, Visual Function Tester (VFT)-lI, Cloud Logic To Opti- Tester (VFT)-lI, Cloud Logic To Opti- Tester (VFT)-lI, Cloud Logic To Opti- mize Use of Defense Systems (CLOUDS)-1A, mize Use of Defense Systems (CLOUDS)-1A, mize Use of Defense Systems (CLOUDS)-1A, Investigations Into Polymer Membrane Process- Investigations Into Polymer Membrane Process- Investigations Into Polymer Membrane Process- ing (IPMP), Shuttle Amateur Radio Experiment ing (IPMP), Shuttle Amateur Radio Experiment ing (IPMP), Shuttle Amateur Radio Experiment (SAREX)-Il, Ultraviolet Plume Instrument (UVPl) (SAREX)-Il, Ultraviolet Plume Instrument (UVPl) (SAREX)-Il, Ultraviolet Plume Instrument (UVPl)

STS-49 Mission Facts — Endeavour — STS-49 Mission Facts — Endeavour — STS-49 Mission Facts — Endeavour — May 7–16, 1992 May 7–16, 1992 May 7–16, 1992

Commander: Daniel C. Brandenstein Commander: Daniel C. Brandenstein Commander: Daniel C. Brandenstein Pilot: Kevin P. Chilton Pilot: Kevin P. Chilton Pilot: Kevin P. Chilton Mission Specialist: Pierre J. Thuot Mission Specialist: Pierre J. Thuot Mission Specialist: Pierre J. Thuot Mission Specialist: Kathryn C. Thornton Mission Specialist: Kathryn C. Thornton Mission Specialist: Kathryn C. Thornton Mission Specialist: Richard J. Hieb Mission Specialist: Richard J. Hieb Mission Specialist: Richard J. Hieb Mission Specialist: Thomas D. Akers Mission Specialist: Thomas D. Akers Mission Specialist: Thomas D. Akers Mission Specialist: Bruce E. Melnick Mission Specialist: Bruce E. Melnick Mission Specialist: Bruce E. Melnick Mission Duration: 192 hours (8 days), 21 hours, Mission Duration: 192 hours (8 days), 21 hours, Mission Duration: 192 hours (8 days), 21 hours, 17 minutes, 39 seconds 17 minutes, 39 seconds 17 minutes, 39 seconds Miles Traveled: Approximately 3,696,019 statute miles Miles Traveled: Approximately 3,696,019 statute miles Miles Traveled: Approximately 3,696,019 statute miles Inclination: 28.35 degrees Inclination: 28.35 degrees Inclination: 28.35 degrees Orbits of Earth: 141 Orbits of Earth: 141 Orbits of Earth: 141 Orbital Altitude: 183 by 95 nautical miles (211 by Orbital Altitude: 183 by 95 nautical miles (211 by Orbital Altitude: 183 by 95 nautical miles (211 by 109 statute miles) minimum orbit 109 statute miles) minimum orbit 109 statute miles) minimum orbit Landing Touchdown: Approximately 2,166 feet beyond Landing Touchdown: Approximately 2,166 feet beyond Landing Touchdown: Approximately 2,166 feet beyond threshold threshold threshold Landing Rollout: Approximately 9,490 feet Landing Rollout: Approximately 9,490 feet Landing Rollout: Approximately 9,490 feet Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately 201,649 pounds 201,649 pounds 201,649 pounds

Y-35 Y-35 Y-35 STS-49 Mission Facts (Cont) STS-49 Mission Facts (Cont) STS-49 Mission Facts (Cont)

Lift-off Weight: Approximately 4,519,238 pounds Lift-off Weight: Approximately 4,519,238 pounds Lift-off Weight: Approximately 4,519,238 pounds Orbiter Weight at Lift-off: Approximately 256,597 Orbiter Weight at Lift-off: Approximately 256,597 Orbiter Weight at Lift-off: Approximately 256,597 pounds pounds pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 198 knots (228 miles per hour) mately 198 knots (228 miles per hour) mately 198 knots (228 miles per hour) Payload Weight Up: Approximately 32,598 pounds Payload Weight Up: Approximately 32,598 pounds Payload Weight Up: Approximately 32,598 pounds Payload Weight Down: Approximately 8,558 pounds Payload Weight Down: Approximately 8,558 pounds Payload Weight Down: Approximately 8,558 pounds Landed: Concrete runway 22 at Edwards Air Force Landed: Concrete runway 22 at Edwards Air Force Landed: Concrete runway 22 at Edwards Air Force Base, California Base, California Base, California Payloads: Intelsat-Vl reboost mission hardware, Assem- Payloads: Intelsat-Vl reboost mission hardware, Assem- Payloads: Intelsat-Vl reboost mission hardware, Assem- bly of Station by EVA Methods (ASEM), Commer- bly of Station by EVA Methods (ASEM), Commer- bly of Station by EVA Methods (ASEM), Commer- cial Protein Crystal Growth (CPCG), Air Force Maui cial Protein Crystal Growth (CPCG), Air Force Maui cial Protein Crystal Growth (CPCG), Air Force Maui Optical Site (AMOS) Calibration Test, Ultraviolet Optical Site (AMOS) Calibration Test, Ultraviolet Optical Site (AMOS) Calibration Test, Ultraviolet Plume Instrument (UVPl) Plume Instrument (UVPl) Plume Instrument (UVPl) Extravehicular Activity (EVA): EVA No. 1, Pierre J. Extravehicular Activity (EVA): EVA No. 1, Pierre J. Extravehicular Activity (EVA): EVA No. 1, Pierre J. Thuot and Richard J. Hieb, 3 hours, 43 minutes Thuot and Richard J. Hieb, 3 hours, 43 minutes Thuot and Richard J. Hieb, 3 hours, 43 minutes duration; EVA No. 2, Pierre J. Thuot and Richard duration; EVA No. 2, Pierre J. Thuot and Richard duration; EVA No. 2, Pierre J. Thuot and Richard J. Hieb, 5 hours, 30 minutes duration; EVA No. 3, J. Hieb, 5 hours, 30 minutes duration; EVA No. 3, J. Hieb, 5 hours, 30 minutes duration; EVA No. 3, Pierre J. Thuot, Richard J. Hieb, and Thomas D. Pierre J. Thuot, Richard J. Hieb, and Thomas D. Pierre J. Thuot, Richard J. Hieb, and Thomas D. Akers, 8 hours, 29 minutes duration (first three- Akers, 8 hours, 29 minutes duration (first three- Akers, 8 hours, 29 minutes duration (first three- person EVA and longest U.S. spacewalk to date); person EVA and longest U.S. spacewalk to date); person EVA and longest U.S. spacewalk to date); and EVA No. 4, Kathryn C. Thornton and Thomas and EVA No. 4, Kathryn C. Thornton and Thomas and EVA No. 4, Kathryn C. Thornton and Thomas D. Akers, 7 hours, 45 minutes duration (most EVAs D. Akers, 7 hours, 45 minutes duration (most EVAs D. Akers, 7 hours, 45 minutes duration (most EVAs on a flight to date). During EVAs 1 and 2, Thuot on a flight to date). During EVAs 1 and 2, Thuot on a flight to date). During EVAs 1 and 2, Thuot and Hieb attempted unsuccessfully to retrieve the and Hieb attempted unsuccessfully to retrieve the and Hieb attempted unsuccessfully to retrieve the Intelsat-Vl satellite using a capture bar. On EVA Intelsat-Vl satellite using a capture bar. On EVA Intelsat-Vl satellite using a capture bar. On EVA 3, Thuot, Hieb, and Akers manually captured the 3, Thuot, Hieb, and Akers manually captured the 3, Thuot, Hieb, and Akers manually captured the satellite, which was subsequently repaired and satellite, which was subsequently repaired and satellite, which was subsequently repaired and redeployed. EVA 4 was used to evaluate Space redeployed. EVA 4 was used to evaluate Space redeployed. EVA 4 was used to evaluate Space Station assembly by EVA methods. Station assembly by EVA methods. Station assembly by EVA methods. First active dual rendezvous of two orbiting spacecraft First active dual rendezvous of two orbiting spacecraft First active dual rendezvous of two orbiting spacecraft (Endeavour and Intelsat-Vl) (Endeavour and Intelsat-Vl) (Endeavour and Intelsat-Vl) First deployment of a drag chute on the orbiter fleet First deployment of a drag chute on the orbiter fleet First deployment of a drag chute on the orbiter fleet

STS-50 Mission Facts — Columbia — STS-50 Mission Facts — Columbia — STS-50 Mission Facts — Columbia — June 25–July 9, 1992 June 25–July 9, 1992 June 25–July 9, 1992

Commander: Richard N. Richards Commander: Richard N. Richards Commander: Richard N. Richards Pilot: Kenneth D. Bowersox Pilot: Kenneth D. Bowersox Pilot: Kenneth D. Bowersox Payload Commander: Bonnie J. Dunbar Payload Commander: Bonnie J. Dunbar Payload Commander: Bonnie J. Dunbar Mission Specialist: Ellen S. Baker Mission Specialist: Ellen S. Baker Mission Specialist: Ellen S. Baker Mission Specialist: Carl J. Meade Mission Specialist: Carl J. Meade Mission Specialist: Carl J. Meade Payload Specialist: Lawrence J. DeLucas Payload Specialist: Lawrence J. DeLucas Payload Specialist: Lawrence J. DeLucas Payload Specialist: Eugene H. Trinh Payload Specialist: Eugene H. Trinh Payload Specialist: Eugene H. Trinh Mission Duration: 312 hours (13 days), 19 hours, 30 Mission Duration: 312 hours (13 days), 19 hours, 30 Mission Duration: 312 hours (13 days), 19 hours, 30 minutes, 4 seconds minutes, 4 seconds minutes, 4 seconds Miles Traveled: Approximately 5,758,000 statute miles Miles Traveled: Approximately 5,758,000 statute miles Miles Traveled: Approximately 5,758,000 statute miles Inclination: 28.45 degrees Inclination: 28.45 degrees Inclination: 28.45 degrees Orbits of Earth: 221 Orbits of Earth: 221 Orbits of Earth: 221 Orbital Altitude: 160 nautical miles (184 statute miles) Orbital Altitude: 160 nautical miles (184 statute miles) Orbital Altitude: 160 nautical miles (184 statute miles) circular orbit circular orbit circular orbit

Y-36 Y-36 Y-36 STS-50 Mission Facts (Cont) STS-50 Mission Facts (Cont) STS-50 Mission Facts (Cont)

Landing Touchdown: Approximately 2,352 feet beyond Landing Touchdown: Approximately 2,352 feet beyond Landing Touchdown: Approximately 2,352 feet beyond threshold threshold threshold Landing Rollout: Approximately 10,674 feet Landing Rollout: Approximately 10,674 feet Landing Rollout: Approximately 10,674 feet Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately 228,127 pounds 228,127 pounds 228,127 pounds Lift-off Weight: Approximately 4,519,680 pounds Lift-off Weight: Approximately 4,519,680 pounds Lift-off Weight: Approximately 4,519,680 pounds Orbiter Weight at Lift-off: Approximately 257,265 Orbiter Weight at Lift-off: Approximately 257,265 Orbiter Weight at Lift-off: Approximately 257,265 pounds pounds pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 209 knots (241 miles per hour) mately 209 knots (241 miles per hour) mately 209 knots (241 miles per hour) Payload Weight Up: Approximately 24,589 pounds Payload Weight Up: Approximately 24,589 pounds Payload Weight Up: Approximately 24,589 pounds Payload Weight Down: Approximately 24,589 pounds Payload Weight Down: Approximately 24,589 pounds Payload Weight Down: Approximately 24,589 pounds Landed: Runway 33 at Kennedy Space Center, Florida Landed: Runway 33 at Kennedy Space Center, Florida Landed: Runway 33 at Kennedy Space Center, Florida Payloads: United States Microgravity Laboratory Payloads: United States Microgravity Laboratory Payloads: United States Microgravity Laboratory (USML)-1; Orbital Acceleration Research (USML)-1; Orbital Acceleration Research (USML)-1; Orbital Acceleration Research Experiment (OARE); Investigations Into Polymer Experiment (OARE); Investigations Into Polymer Experiment (OARE); Investigations Into Polymer Membrane Processing (IPMP), Shuttle Amateur Membrane Processing (IPMP), Shuttle Amateur Membrane Processing (IPMP), Shuttle Amateur Radio Experiment (SAREX)-ll; Ultraviolet Plume Radio Experiment (SAREX)-ll; Ultraviolet Plume Radio Experiment (SAREX)-ll; Ultraviolet Plume Instrument (UVPl) Instrument (UVPl) Instrument (UVPl) First extended-duration mission First extended-duration mission First extended-duration mission

STS-46 Mission Facts — Atlantis — STS-46 Mission Facts — Atlantis — STS-46 Mission Facts — Atlantis — July 31–August 8, 1992 July 31–August 8, 1992 July 31–August 8, 1992

Commander: Loren J. Shriver Commander: Loren J. Shriver Commander: Loren J. Shriver Pilot: Andrew M. Allen Pilot: Andrew M. Allen Pilot: Andrew M. Allen Payload Commander: Jeffrey A. Hoffman Payload Commander: Jeffrey A. Hoffman Payload Commander: Jeffrey A. Hoffman Mission Specialist: Franklin R. Chang-Diaz Mission Specialist: Franklin R. Chang-Diaz Mission Specialist: Franklin R. Chang-Diaz Mission Specialist: Claude Nicollier Mission Specialist: Claude Nicollier Mission Specialist: Claude Nicollier Mission Specialist: Marsha S. Ivins Mission Specialist: Marsha S. Ivins Mission Specialist: Marsha S. Ivins Payload Specialist: Dr. Franco Malerbo Payload Specialist: Dr. Franco Malerbo Payload Specialist: Dr. Franco Malerbo Mission Duration: 168 hours (7 days), 23 hours, Mission Duration: 168 hours (7 days), 23 hours, Mission Duration: 168 hours (7 days), 23 hours, 16 minutes, 7 seconds 16 minutes, 7 seconds 16 minutes, 7 seconds Miles Traveled: Approximately 3,321,007 statute miles Miles Traveled: Approximately 3,321,007 statute miles Miles Traveled: Approximately 3,321,007 statute miles Inclination: 28.45 degrees Inclination: 28.45 degrees Inclination: 28.45 degrees Orbits of Earth: 127 Orbits of Earth: 127 Orbits of Earth: 127 Orbital Altitude: 127 nautical miles (146 statute miles) Orbital Altitude: 127 nautical miles (146 statute miles) Orbital Altitude: 127 nautical miles (146 statute miles) circular orbit circular orbit circular orbit Landing Touchdown: Approximately 1,950 feet beyond Landing Touchdown: Approximately 1,950 feet beyond Landing Touchdown: Approximately 1,950 feet beyond threshold threshold threshold Landing Rollout: Approximately 10,860 feet Landing Rollout: Approximately 10,860 feet Landing Rollout: Approximately 10,860 feet Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately 208,806 pounds 208,806 pounds 208,806 pounds Lift-off Weight: Approximately 4,516,789 pounds Lift-off Weight: Approximately 4,516,789 pounds Lift-off Weight: Approximately 4,516,789 pounds Orbiter Weight at Lift-off: Approximately 256,031 Orbiter Weight at Lift-off: Approximately 256,031 Orbiter Weight at Lift-off: Approximately 256,031 pounds pounds pounds Landing Speed at Main Gear Touchdown: Landing Speed at Main Gear Touchdown: Landing Speed at Main Gear Touchdown: Approximately 204 knots (234 miles per hour) Approximately 204 knots (234 miles per hour) Approximately 204 knots (234 miles per hour) Payload Weight Up: Approximately 28,585 pounds Payload Weight Up: Approximately 28,585 pounds Payload Weight Up: Approximately 28,585 pounds Payload Weight Down: Approximately 18,594 pounds Payload Weight Down: Approximately 18,594 pounds Payload Weight Down: Approximately 18,594 pounds

Y-37 Y-37 Y-37 STS-46 Mission Facts (Cont) STS-46 Mission Facts (Cont) STS-46 Mission Facts (Cont)

Landed: Runway 33 at Kennedy Space Center, Florida Landed: Runway 33 at Kennedy Space Center, Florida Landed: Runway 33 at Kennedy Space Center, Florida Payloads: Tethered Satellite System (TSS)-1; European Payloads: Tethered Satellite System (TSS)-1; European Payloads: Tethered Satellite System (TSS)-1; European Retrievable Carrier (EURECA)-1L; Evaluation of Retrievable Carrier (EURECA)-1L; Evaluation of Retrievable Carrier (EURECA)-1L; Evaluation of Oxygen Integration with Materials (EOlM)-lll/ Oxygen Integration with Materials (EOlM)-lll/ Oxygen Integration with Materials (EOlM)-lll/ Thermal Energy Management Processes Thermal Energy Management Processes Thermal Energy Management Processes (TEMP)-2A; Consortium for Materials Development (TEMP)-2A; Consortium for Materials Development (TEMP)-2A; Consortium for Materials Development In Space Complex Autonomous Payloads (CON- In Space Complex Autonomous Payloads (CON- In Space Complex Autonomous Payloads (CON- CAP)-ll and Ill; IMAX Cargo Bay Camera (ICBC); CAP)-ll and Ill; IMAX Cargo Bay Camera (ICBC); CAP)-ll and Ill; IMAX Cargo Bay Camera (ICBC); Limited Duration Space Environment Candidate Limited Duration Space Environment Candidate Limited Duration Space Environment Candidate Materials Exposure (LDCE); Pituitary Growth Materials Exposure (LDCE); Pituitary Growth Materials Exposure (LDCE); Pituitary Growth Hormone Cell Function (PHCF); Ultraviolet Plume Hormone Cell Function (PHCF); Ultraviolet Plume Hormone Cell Function (PHCF); Ultraviolet Plume Instrument (UVPl) Instrument (UVPl) Instrument (UVPl)

STS-47 Mission Facts — Endeavour — STS-47 Mission Facts — Endeavour — STS-47 Mission Facts — Endeavour — September 12–20, 1992 September 12–20, 1992 September 12–20, 1992

Commander: Robert L. Gibson Commander: Robert L. Gibson Commander: Robert L. Gibson Pilot: Curtis L. Brown, Jr. Pilot: Curtis L. Brown, Jr. Pilot: Curtis L. Brown, Jr. Mission Specialist: Mark C. Lee Mission Specialist: Mark C. Lee Mission Specialist: Mark C. Lee Mission Specialist: Jerome Apt Mission Specialist: Jerome Apt Mission Specialist: Jerome Apt Mission Specialist: N. Jan Davis Mission Specialist: N. Jan Davis Mission Specialist: N. Jan Davis Mission Specialist: Dr. Mae C. Jemison Mission Specialist: Dr. Mae C. Jemison Mission Specialist: Dr. Mae C. Jemison Payload Specialist: Mamoru Mohri Payload Specialist: Mamoru Mohri Payload Specialist: Mamoru Mohri Mission Duration: 168 hours (7 days), 22 hours, Mission Duration: 168 hours (7 days), 22 hours, Mission Duration: 168 hours (7 days), 22 hours, 31 minutes, 11 seconds 31 minutes, 11 seconds 31 minutes, 11 seconds Miles Traveled: Approximately 3,310,922 statute miles Miles Traveled: Approximately 3,310,922 statute miles Miles Traveled: Approximately 3,310,922 statute miles Inclination: 57 degrees Inclination: 57 degrees Inclination: 57 degrees Orbits of Earth: 127 Orbits of Earth: 127 Orbits of Earth: 127 Orbital Altitude: 163 nautical miles (188 statute miles) Orbital Altitude: 163 nautical miles (188 statute miles) Orbital Altitude: 163 nautical miles (188 statute miles) circular orbit circular orbit circular orbit Landing Touchdown: Approximately 2,458 feet beyond Landing Touchdown: Approximately 2,458 feet beyond Landing Touchdown: Approximately 2,458 feet beyond threshold threshold threshold Landing Rollout: Approximately 8,567 feet Landing Rollout: Approximately 8,567 feet Landing Rollout: Approximately 8,567 feet Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately 219,327 pounds 219,327 pounds 219,327 pounds Lift-off Weight: Approximately 4,506,649 pounds Lift-off Weight: Approximately 4,506,649 pounds Lift-off Weight: Approximately 4,506,649 pounds Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately 244,413 pounds 244,413 pounds 244,413 pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 211 knots (243 miles per hour) mately 211 knots (243 miles per hour) mately 211 knots (243 miles per hour) Payload Weight Up: Approximately 28,158 pounds Payload Weight Up: Approximately 28,158 pounds Payload Weight Up: Approximately 28,158 pounds Payload Weight Down: Approximately 28,158 pounds Payload Weight Down: Approximately 28,158 pounds Payload Weight Down: Approximately 28,158 pounds Landed: Runway 33 at Kennedy Space Center, Florida Landed: Runway 33 at Kennedy Space Center, Florida Landed: Runway 33 at Kennedy Space Center, Florida Payloads: Spacelab-J, nine getaway special canister Payloads: Spacelab-J, nine getaway special canister Payloads: Spacelab-J, nine getaway special canister experiments, Israel Space Agency Investigation experiments, Israel Space Agency Investigation experiments, Israel Space Agency Investigation About Hornets (ISAIAH), Shuttle Amateur Radio About Hornets (ISAIAH), Shuttle Amateur Radio About Hornets (ISAIAH), Shuttle Amateur Radio Experiment (SAREX) II, Solid Surface Combustion Experiment (SAREX) II, Solid Surface Combustion Experiment (SAREX) II, Solid Surface Combustion Experiment (SSCE) Experiment (SSCE) Experiment (SSCE)

Y-38 Y-38 Y-38 STS-52 Mission Facts — Columbia — STS-52 Mission Facts — Columbia — STS-52 Mission Facts — Columbia — October 22–November 1, 1992 October 22–November 1, 1992 October 22–November 1, 1992

Commander: James D. Wetherbee Commander: James D. Wetherbee Commander: James D. Wetherbee Pilot: Michael A. Baker Pilot: Michael A. Baker Pilot: Michael A. Baker Mission Specialist: William M. Shepherd Mission Specialist: William M. Shepherd Mission Specialist: William M. Shepherd Mission Specialist: Tamara E. Jernigan Mission Specialist: Tamara E. Jernigan Mission Specialist: Tamara E. Jernigan Mission Specialist: Charles Lacy Veach Mission Specialist: Charles Lacy Veach Mission Specialist: Charles Lacy Veach Payload Specialist: Steven MacLean Payload Specialist: Steven MacLean Payload Specialist: Steven MacLean Mission Duration: 216 hours (9 days), 20 hours, Mission Duration: 216 hours (9 days), 20 hours, Mission Duration: 216 hours (9 days), 20 hours, 56 minutes, 13 seconds 56 minutes, 13 seconds 56 minutes, 13 seconds Miles Traveled: Approximately 4,129,028 statute miles Miles Traveled: Approximately 4,129,028 statute miles Miles Traveled: Approximately 4,129,028 statute miles Inclination: 28.45 degrees Inclination: 28.45 degrees Inclination: 28.45 degrees Orbits of Earth: 159 Orbits of Earth: 159 Orbits of Earth: 159 Orbital Altitude: 160 nautical miles (184 statute miles) Orbital Altitude: 160 nautical miles (184 statute miles) Orbital Altitude: 160 nautical miles (184 statute miles) circular orbit, then 155 nautical miles (178 statute circular orbit, then 155 nautical miles (178 statute circular orbit, then 155 nautical miles (178 statute miles) circular orbit, then 113 nautical miles miles) circular orbit, then 113 nautical miles miles) circular orbit, then 113 nautical miles (130 statute miles) circular orbit (130 statute miles) circular orbit (130 statute miles) circular orbit Landing Touchdown: Approximately 1,080 feet beyond Landing Touchdown: Approximately 1,080 feet beyond Landing Touchdown: Approximately 1,080 feet beyond threshold threshold threshold Landing Rollout: Approximately 10,708 feet Landing Rollout: Approximately 10,708 feet Landing Rollout: Approximately 10,708 feet Orbiter Weight at Landing: Approximately 215,114 Orbiter Weight at Landing: Approximately 215,114 Orbiter Weight at Landing: Approximately 215,114 pounds pounds pounds Lift-off Weight: Approximately 4,514,325 pounds Lift-off Weight: Approximately 4,514,325 pounds Lift-off Weight: Approximately 4,514,325 pounds Orbiter Weight at Lift-off: Approximately 250,130 Orbiter Weight at Lift-off: Approximately 250,130 Orbiter Weight at Lift-off: Approximately 250,130 pounds pounds pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 211 knots (243 miles per hour) mately 211 knots (243 miles per hour) mately 211 knots (243 miles per hour) Payload Weight Up: Approximately 20,077 pounds Payload Weight Up: Approximately 20,077 pounds Payload Weight Up: Approximately 20,077 pounds Payload Weight Down: Approximately 14,419 pounds Payload Weight Down: Approximately 14,419 pounds Payload Weight Down: Approximately 14,419 pounds Landed: Runway 33 at Kennedy Space Center, Florida Landed: Runway 33 at Kennedy Space Center, Florida Landed: Runway 33 at Kennedy Space Center, Florida Payloads: Laser Geodynamic Satellite (LAGEOS) Payloads: Laser Geodynamic Satellite (LAGEOS) Payloads: Laser Geodynamic Satellite (LAGEOS) II/Italian Research Interim Stage (IRIS), Canadian II/Italian Research Interim Stage (IRIS), Canadian II/Italian Research Interim Stage (IRIS), Canadian Experiments (CANEX) 2, United States Micro- Experiments (CANEX) 2, United States Micro- Experiments (CANEX) 2, United States Micro- gravity Payload (USMP) 1, Attitude Sensor Pack- gravity Payload (USMP) 1, Attitude Sensor Pack- gravity Payload (USMP) 1, Attitude Sensor Pack- age (ASP), Tank Pressure Control Experiment age (ASP), Tank Pressure Control Experiment age (ASP), Tank Pressure Control Experiment (TPCE), Physiological Systems Experiment (PSE), (TPCE), Physiological Systems Experiment (PSE), (TPCE), Physiological Systems Experiment (PSE), Heat Pipe Performance (HPP) experiment, Com- Heat Pipe Performance (HPP) experiment, Com- Heat Pipe Performance (HPP) experiment, Com- mercial Protein Crystal Growth (CPCG), Shuttle mercial Protein Crystal Growth (CPCG), Shuttle mercial Protein Crystal Growth (CPCG), Shuttle Plume Impingement Experiment (SPIE), Commer- Plume Impingement Experiment (SPIE), Commer- Plume Impingement Experiment (SPIE), Commer- cial Materials ITA Experiment (CMIX), Crystals by cial Materials ITA Experiment (CMIX), Crystals by cial Materials ITA Experiment (CMIX), Crystals by Vapor Transport Experiment (CVTE) Vapor Transport Experiment (CVTE) Vapor Transport Experiment (CVTE)

STS-53 Mission Facts — Discovery — STS-53 Mission Facts — Discovery — STS-53 Mission Facts — Discovery — December 2–9, 1992 December 2–9, 1992 December 2–9, 1992

Commander: David M. Walker Commander: David M. Walker Commander: David M. Walker Pilot: Robert D. Cabana Pilot: Robert D. Cabana Pilot: Robert D. Cabana Mission Specialist: Guion S. Bluford Mission Specialist: Guion S. Bluford Mission Specialist: Guion S. Bluford Mission Specialist: James S. Voss Mission Specialist: James S. Voss Mission Specialist: James S. Voss Mission Specialist: Michael Richard “Rich” V. Clifford Mission Specialist: Michael Richard “Rich” V. Clifford Mission Specialist: Michael Richard “Rich” V. Clifford Mission Duration: 168 hours (7 days), 7 hours, Mission Duration: 168 hours (7 days), 7 hours, Mission Duration: 168 hours (7 days), 7 hours, 19 minutes, 17 seconds 19 minutes, 17 seconds 19 minutes, 17 seconds

Y-39 Y-39 Y-39 STS-53 Mission Facts (Cont) STS-53 Mission Facts (Cont) STS-53 Mission Facts (Cont)

Miles Traveled: Approximately 3,034,680 statute miles Miles Traveled: Approximately 3,034,680 statute miles Miles Traveled: Approximately 3,034,680 statute miles Inclination: 57 degrees Inclination: 57 degrees Inclination: 57 degrees Orbits of Earth: 116 Orbits of Earth: 116 Orbits of Earth: 116 Orbital Altitude: 200 nautical miles (230 statute miles) Orbital Altitude: 200 nautical miles (230 statute miles) Orbital Altitude: 200 nautical miles (230 statute miles) circular orbit (DOD-1 deployment), then 175 nauti- circular orbit (DOD-1 deployment), then 175 nauti- circular orbit (DOD-1 deployment), then 175 nauti- cal miles (202 statute miles) circular orbit (ODER- cal miles (202 statute miles) circular orbit (ODER- cal miles (202 statute miles) circular orbit (ODER- ACS deployment) ACS deployment) ACS deployment) Landing Touchdown: Approximately 1,190 feet beyond Landing Touchdown: Approximately 1,190 feet beyond Landing Touchdown: Approximately 1,190 feet beyond threshold threshold threshold Landing Rollout: Approximately 10,165 feet Landing Rollout: Approximately 10,165 feet Landing Rollout: Approximately 10,165 feet Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately 193,215 pounds 193,215 pounds 193,215 pounds Lift-off Weight: Approximately 4,506,642 pounds Lift-off Weight: Approximately 4,506,642 pounds Lift-off Weight: Approximately 4,506,642 pounds Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately 243,952 pounds 243,952 pounds 243,952 pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 209 knots (241 miles per hour) mately 209 knots (241 miles per hour) mately 209 knots (241 miles per hour) Payload Weight Up: Approximately 26,166 pounds Payload Weight Up: Approximately 26,166 pounds Payload Weight Up: Approximately 26,166 pounds Payload Weight Down: Approximately 5,151 pounds Payload Weight Down: Approximately 5,151 pounds Payload Weight Down: Approximately 5,151 pounds Landed: Concrete Runway 22 at Edwards Air Force Landed: Concrete Runway 22 at Edwards Air Force Landed: Concrete Runway 22 at Edwards Air Force Base, California Base, California Base, California Payloads: Department of Defense (DOD)1; Glow Experi- Payloads: Department of Defense (DOD)1; Glow Experi- Payloads: Department of Defense (DOD)1; Glow Experi- ment/Cryogenic Heat Pipe Experiment Payload ment/Cryogenic Heat Pipe Experiment Payload ment/Cryogenic Heat Pipe Experiment Payload (GCP); Orbital Debris Radar Calibration System (GCP); Orbital Debris Radar Calibration System (GCP); Orbital Debris Radar Calibration System (ODERACS); Battlefield Laser Acquisition Sensor (ODERACS); Battlefield Laser Acquisition Sensor (ODERACS); Battlefield Laser Acquisition Sensor Test (BLAST); Cloud Logic To Optimize Use of Test (BLAST); Cloud Logic To Optimize Use of Test (BLAST); Cloud Logic To Optimize Use of Defense Systems (CLOUDS) 1A; Cosmic Radia- Defense Systems (CLOUDS) 1A; Cosmic Radia- Defense Systems (CLOUDS) 1A; Cosmic Radia- tion Effects and Activation Monitor (CREAM); Fluid tion Effects and Activation Monitor (CREAM); Fluid tion Effects and Activation Monitor (CREAM); Fluid Acquisition and Resupply Equipment (FARE); Acquisition and Resupply Equipment (FARE); Acquisition and Resupply Equipment (FARE); Hand-held, Earth-oriented, Real-time, Coopera- Hand-held, Earth-oriented, Real-time, Coopera- Hand-held, Earth-oriented, Real-time, Coopera- tive, User-friendly, Location-targeting and Environ- tive, User-friendly, Location-targeting and Environ- tive, User-friendly, Location-targeting and Environ- mental System (HERCULES); Microencapsulation mental System (HERCULES); Microencapsulation mental System (HERCULES); Microencapsulation in Space (MIS)-1; Radiation Monitoring Equipment in Space (MIS)-1; Radiation Monitoring Equipment in Space (MIS)-1; Radiation Monitoring Equipment (RME) III; Spare Tissue Loss (STL); Visual Function (RME) III; Spare Tissue Loss (STL); Visual Function (RME) III; Spare Tissue Loss (STL); Visual Function Tester (VFT)2. The ODERACS payload was unable Tester (VFT)2. The ODERACS payload was unable Tester (VFT)2. The ODERACS payload was unable to be deployed because of payload equipment to be deployed because of payload equipment to be deployed because of payload equipment malfunction. malfunction. malfunction.

STS-54 Mission Facts — Endeavour — STS-54 Mission Facts — Endeavour — STS-54 Mission Facts — Endeavour — January 13–19, 1993 January 13–19, 1993 January 13–19, 1993

Commander: John H. Casper Commander: John H. Casper Commander: John H. Casper Pilot: Donald R. McMonagle Pilot: Donald R. McMonagle Pilot: Donald R. McMonagle Mission Specialist 1: Mario Runco, Jr. Mission Specialist 1: Mario Runco, Jr. Mission Specialist 1: Mario Runco, Jr. Mission Specialist 2: Gregory J. Harbaugh Mission Specialist 2: Gregory J. Harbaugh Mission Specialist 2: Gregory J. Harbaugh Mission Specialist 3: Susan J. Helms Mission Specialist 3: Susan J. Helms Mission Specialist 3: Susan J. Helms Mission Duration: 120 hours (5 days), 23 hours, Mission Duration: 120 hours (5 days), 23 hours, Mission Duration: 120 hours (5 days), 23 hours, 38 minutes, 17 seconds 38 minutes, 17 seconds 38 minutes, 17 seconds Miles Traveled: Approximately 2,501,277 statute miles Miles Traveled: Approximately 2,501,277 statute miles Miles Traveled: Approximately 2,501,277 statute miles Inclination: 28.45 degrees Inclination: 28.45 degrees Inclination: 28.45 degrees Orbits of Earth: 96 Orbits of Earth: 96 Orbits of Earth: 96

Y-40 Y-40 Y-40 STS-54 Mission Facts (Cont) STS-54 Mission Facts (Cont) STS-54 Mission Facts (Cont)

Orbital Altitude: 160 nautical miles (184 statute miles) Orbital Altitude: 160 nautical miles (184 statute miles) Orbital Altitude: 160 nautical miles (184 statute miles) circular orbit circular orbit circular orbit Landing Touchdown: Approximately 1,500 feet beyond Landing Touchdown: Approximately 1,500 feet beyond Landing Touchdown: Approximately 1,500 feet beyond threshold threshold threshold Landing Rollout: Approximately 8,700 feet Landing Rollout: Approximately 8,700 feet Landing Rollout: Approximately 8,700 feet Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately 197,778 pounds 197,778 pounds 197,778 pounds Lift-off Weight: Approximately 4,522,692 pounds Lift-off Weight: Approximately 4,522,692 pounds Lift-off Weight: Approximately 4,522,692 pounds Orbiter Weight at Lift-off: Approximately 259,264 Orbiter Weight at Lift-off: Approximately 259,264 Orbiter Weight at Lift-off: Approximately 259,264 pounds pounds pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 205 knots (236 miles per hour) mately 205 knots (236 miles per hour) mately 205 knots (236 miles per hour) Payload Weight Up: Approximately 46,643 pounds Payload Weight Up: Approximately 46,643 pounds Payload Weight Up: Approximately 46,643 pounds Payload Weight Down: Approximately 9,068 pounds Payload Weight Down: Approximately 9,068 pounds Payload Weight Down: Approximately 9,068 pounds Landed: Concrete Runway 33 at Kennedy Space Cen- Landed: Concrete Runway 33 at Kennedy Space Cen- Landed: Concrete Runway 33 at Kennedy Space Cen- ter, Florida ter, Florida ter, Florida Extravehicular Activity (EVA): Gregory J. Harbaugh Extravehicular Activity (EVA): Gregory J. Harbaugh Extravehicular Activity (EVA): Gregory J. Harbaugh and Mario Runco, Jr. Duration 4 hours, 27 minutes, and Mario Runco, Jr. Duration 4 hours, 27 minutes, and Mario Runco, Jr. Duration 4 hours, 27 minutes, 50 seconds 50 seconds 50 seconds Payloads: Tracking and Data Relay Satellite Payloads: Tracking and Data Relay Satellite Payloads: Tracking and Data Relay Satellite (TDRS)-F/Inertial Upper Stage (IUS); Diffuse (TDRS)-F/Inertial Upper Stage (IUS); Diffuse (TDRS)-F/Inertial Upper Stage (IUS); Diffuse X-ray Spectrometer (DXS); Chromosome and X-ray Spectrometer (DXS); Chromosome and X-ray Spectrometer (DXS); Chromosome and Plant Cell Division in Space (CHROMEX); Com- Plant Cell Division in Space (CHROMEX); Com- Plant Cell Division in Space (CHROMEX); Com- mercial Generic Bioprocessing Apparatus (CGBA) mercial Generic Bioprocessing Apparatus (CGBA) mercial Generic Bioprocessing Apparatus (CGBA) A; Physiological and Anatomical Rodent A; Physiological and Anatomical Rodent A; Physiological and Anatomical Rodent Experiment (PARE) 02; Solid Surface Combustion Experiment (PARE) 02; Solid Surface Combustion Experiment (PARE) 02; Solid Surface Combustion Experiment (SSCE) Experiment (SSCE) Experiment (SSCE)

STS-56 Mission Facts — Discovery — STS-56 Mission Facts — Discovery — STS-56 Mission Facts — Discovery — April 8–17, 1993 April 8–17, 1993 April 8–17, 1993

Commander: Kenneth Cameron Commander: Kenneth Cameron Commander: Kenneth Cameron Pilot: Stephen S. Oswald Pilot: Stephen S. Oswald Pilot: Stephen S. Oswald Mission Specialist 1: Michael Foale Mission Specialist 1: Michael Foale Mission Specialist 1: Michael Foale Mission Specialist 2: Kenneth D. Cockrell Mission Specialist 2: Kenneth D. Cockrell Mission Specialist 2: Kenneth D. Cockrell Mission Specialist 3: Ellen Ochoa Mission Specialist 3: Ellen Ochoa Mission Specialist 3: Ellen Ochoa Mission Duration: 216 hours (9 days) 6 hours, Mission Duration: 216 hours (9 days) 6 hours, Mission Duration: 216 hours (9 days) 6 hours, 8 minutes, 23 seconds 8 minutes, 23 seconds 8 minutes, 23 seconds Miles Traveled: Approximately 3,853,997 statute miles Miles Traveled: Approximately 3,853,997 statute miles Miles Traveled: Approximately 3,853,997 statute miles Inclination: 57 degrees Inclination: 57 degrees Inclination: 57 degrees Orbits of Earth: 148 Orbits of Earth: 148 Orbits of Earth: 148 Orbital Altitude: 160 nautical miles (184 statute miles) Orbital Altitude: 160 nautical miles (184 statute miles) Orbital Altitude: 160 nautical miles (184 statute miles) circular orbit circular orbit circular orbit Landing Touchdown: Approximately 1,075 feet beyond Landing Touchdown: Approximately 1,075 feet beyond Landing Touchdown: Approximately 1,075 feet beyond threshold threshold threshold Landing Rollout: Approximately 9,529 feet Landing Rollout: Approximately 9,529 feet Landing Rollout: Approximately 9,529 feet Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately 206,855 pounds 206,855 pounds 206,855 pounds Lift-off Weight: Approximately 4,500,815 pounds Lift-off Weight: Approximately 4,500,815 pounds Lift-off Weight: Approximately 4,500,815 pounds Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately 236,659 pounds 236,659 pounds 236,659 pounds

Y-41 Y-41 Y-41 STS-56 Mission Facts (Cont) STS-56 Mission Facts (Cont) STS-56 Mission Facts (Cont)

Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 196 knots (226 miles per hour) mately 196 knots (226 miles per hour) mately 196 knots (226 miles per hour) Payload Weight Up: Approximately 16,406 pounds Payload Weight Up: Approximately 16,406 pounds Payload Weight Up: Approximately 16,406 pounds Payload Weight Down: Approximately 16,406 pounds Payload Weight Down: Approximately 16,406 pounds Payload Weight Down: Approximately 16,406 pounds Landed: Concrete runway 33 at Kennedy Space Center, Landed: Concrete runway 33 at Kennedy Space Center, Landed: Concrete runway 33 at Kennedy Space Center, Florida Florida Florida Payloads: Atmospheric Laboratory for Applications Payloads: Atmospheric Laboratory for Applications Payloads: Atmospheric Laboratory for Applications and Science (ATLAS) 2, Shuttle Solar Backscatter and Science (ATLAS) 2, Shuttle Solar Backscatter and Science (ATLAS) 2, Shuttle Solar Backscatter Ultraviolet (SSBUV) A, Shuttle Pointed Autono- Ultraviolet (SSBUV) A, Shuttle Pointed Autono- Ultraviolet (SSBUV) A, Shuttle Pointed Autono- mous Research Tool for Astronomy (SPARTAN) mous Research Tool for Astronomy (SPARTAN) mous Research Tool for Astronomy (SPARTAN) 201 (Solar Wind Generation Experiment), Solar 201 (Solar Wind Generation Experiment), Solar 201 (Solar Wind Generation Experiment), Solar Ultraviolet Experiment (SUVE), Commercial Mate- Ultraviolet Experiment (SUVE), Commercial Mate- Ultraviolet Experiment (SUVE), Commercial Mate- rial Dispersion Apparatus (CMIX), Physiological rial Dispersion Apparatus (CMIX), Physiological rial Dispersion Apparatus (CMIX), Physiological and Anatomical Rodent Experiment (PARE), Hand- and Anatomical Rodent Experiment (PARE), Hand- and Anatomical Rodent Experiment (PARE), Hand- held, Earth-oriented, Real-time, Cooperative, held, Earth-oriented, Real-time, Cooperative, held, Earth-oriented, Real-time, Cooperative, User-friendly, Location-targeting, and Environ- User-friendly, Location-targeting, and Environ- User-friendly, Location-targeting, and Environ- mental System (HERCULES), Shuttle Amateur mental System (HERCULES), Shuttle Amateur mental System (HERCULES), Shuttle Amateur Radio Experiment (SAREX) II, Space Tissue Loss Radio Experiment (SAREX) II, Space Tissue Loss Radio Experiment (SAREX) II, Space Tissue Loss (STL), Air Force Maui Optical Site (AMOS), Cosmic (STL), Air Force Maui Optical Site (AMOS), Cosmic (STL), Air Force Maui Optical Site (AMOS), Cosmic Radiation Effects and Activation Monitor (CREAM), Radiation Effects and Activation Monitor (CREAM), Radiation Effects and Activation Monitor (CREAM), Radiation Monitoring Equipment (RME) III Radiation Monitoring Equipment (RME) III Radiation Monitoring Equipment (RME) III

STS-55 Mission Facts — Columbia — STS-55 Mission Facts — Columbia — STS-55 Mission Facts — Columbia — April 26–May 6, 1993 April 26–May 6, 1993 April 26–May 6, 1993

Commander: Steven R. Nagel Commander: Steven R. Nagel Commander: Steven R. Nagel Pilot: Terrence T. Henricks Pilot: Terrence T. Henricks Pilot: Terrence T. Henricks Payload Commander: Jerry L. Ross Payload Commander: Jerry L. Ross Payload Commander: Jerry L. Ross Mission Specialist 2: Charles J. Precourt Mission Specialist 2: Charles J. Precourt Mission Specialist 2: Charles J. Precourt Mission Specialist 3: Bernard A. Harris, Jr. Mission Specialist 3: Bernard A. Harris, Jr. Mission Specialist 3: Bernard A. Harris, Jr. Payload Specialist 1: Ulrich Walter, Germany Payload Specialist 1: Ulrich Walter, Germany Payload Specialist 1: Ulrich Walter, Germany Payload Specialist 2: Hans Schlegel, Germany Payload Specialist 2: Hans Schlegel, Germany Payload Specialist 2: Hans Schlegel, Germany Mission Duration: 216 hours (9 days) 23 hours, Mission Duration: 216 hours (9 days) 23 hours, Mission Duration: 216 hours (9 days) 23 hours, 39 minutes, 59 seconds 39 minutes, 59 seconds 39 minutes, 59 seconds Miles Traveled: Approximately 4,164,183 statute miles Miles Traveled: Approximately 4,164,183 statute miles Miles Traveled: Approximately 4,164,183 statute miles Inclination: 28.45 degrees Inclination: 28.45 degrees Inclination: 28.45 degrees Orbits of Earth: 160 Orbits of Earth: 160 Orbits of Earth: 160 Orbital Altitude: 160 nautical miles (184 statute miles) Orbital Altitude: 160 nautical miles (184 statute miles) Orbital Altitude: 160 nautical miles (184 statute miles) circular orbit circular orbit circular orbit Landing Touchdown: Approximately 1,819 feet beyond Landing Touchdown: Approximately 1,819 feet beyond Landing Touchdown: Approximately 1,819 feet beyond threshold threshold threshold Landing Rollout: Approximately 10,125 feet Landing Rollout: Approximately 10,125 feet Landing Rollout: Approximately 10,125 feet Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately 227,203 pounds 227,203 pounds 227,203 pounds Lift-off Weight: Approximately 4,518,784 pounds Lift-off Weight: Approximately 4,518,784 pounds Lift-off Weight: Approximately 4,518,784 pounds Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately 255,252 pounds 255,252 pounds 255,252 pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 210 knots (242 miles per hour) mately 210 knots (242 miles per hour) mately 210 knots (242 miles per hour) Payload Weight Up: Approximately 26,864 pounds Payload Weight Up: Approximately 26,864 pounds Payload Weight Up: Approximately 26,864 pounds

Y-42 Y-42 Y-42 STS-55 Mission Facts (Cont) STS-55 Mission Facts (Cont) STS-55 Mission Facts (Cont)

Payload Weight Down: Approximately 26,864 pounds Payload Weight Down: Approximately 26,864 pounds Payload Weight Down: Approximately 26,864 pounds Landed: Concrete runway 22 at Edwards Air Force Landed: Concrete runway 22 at Edwards Air Force Landed: Concrete runway 22 at Edwards Air Force Base, California Base, California Base, California Payloads: Spacelab D-2 with long module, unique Payloads: Spacelab D-2 with long module, unique Payloads: Spacelab D-2 with long module, unique support structure (USS), and Reaction Kinetics support structure (USS), and Reaction Kinetics support structure (USS), and Reaction Kinetics in Glass Melts (RKGM) getaway special, Shuttle in Glass Melts (RKGM) getaway special, Shuttle in Glass Melts (RKGM) getaway special, Shuttle Amateur Radio Experiment (SAREX) II Amateur Radio Experiment (SAREX) II Amateur Radio Experiment (SAREX) II

STS-57 Mission Facts — Endeavour — STS-57 Mission Facts — Endeavour — STS-57 Mission Facts — Endeavour — June 21–July 1, 1993 June 21–July 1, 1993 June 21–July 1, 1993

Commander: Ronald J. Grabe Commander: Ronald J. Grabe Commander: Ronald J. Grabe Pilot: Brian J. Duffy Pilot: Brian J. Duffy Pilot: Brian J. Duffy Payload Commander: G. David Low Payload Commander: G. David Low Payload Commander: G. David Low Mission Specialist 2: Nancy J. Sherlock Mission Specialist 2: Nancy J. Sherlock Mission Specialist 2: Nancy J. Sherlock Mission Specialist 3: Peter J.K. “Jeff” Wisoff Mission Specialist 3: Peter J.K. “Jeff” Wisoff Mission Specialist 3: Peter J.K. “Jeff” Wisoff Mission Specialist 4: Janice E. Voss Mission Specialist 4: Janice E. Voss Mission Specialist 4: Janice E. Voss Mission Duration: 216 hours (9 days), 23 hours, Mission Duration: 216 hours (9 days), 23 hours, Mission Duration: 216 hours (9 days), 23 hours, 44 minutes, 54 seconds 44 minutes, 54 seconds 44 minutes, 54 seconds Miles Traveled: Approximately 4,118,037 statute miles Miles Traveled: Approximately 4,118,037 statute miles Miles Traveled: Approximately 4,118,037 statute miles Inclination: 28.45 degrees Inclination: 28.45 degrees Inclination: 28.45 degrees Orbits of Earth: 155 Orbits of Earth: 155 Orbits of Earth: 155 Orbital Altitude: 250 nautical miles (287 statute miles) Orbital Altitude: 250 nautical miles (287 statute miles) Orbital Altitude: 250 nautical miles (287 statute miles) circular orbit circular orbit circular orbit Landing Touchdown: Approximately 2,305 feet beyond Landing Touchdown: Approximately 2,305 feet beyond Landing Touchdown: Approximately 2,305 feet beyond threshold threshold threshold Landing Rollout: Approximately 9,946 feet Landing Rollout: Approximately 9,946 feet Landing Rollout: Approximately 9,946 feet Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately 244,400 pounds 244,400 pounds 244,400 pounds Lift-off Weight: Approximately 4,516,459 pounds Lift-off Weight: Approximately 4,516,459 pounds Lift-off Weight: Approximately 4,516,459 pounds Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately 252,359 pounds 252,359 pounds 252,359 pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 200 knots (230 miles per hour) mately 200 knots (230 miles per hour) mately 200 knots (230 miles per hour) Payload Weight Up: Approximately 19,691 pounds Payload Weight Up: Approximately 19,691 pounds Payload Weight Up: Approximately 19,691 pounds Payload Weight Down: Approximately 28,925 pounds Payload Weight Down: Approximately 28,925 pounds Payload Weight Down: Approximately 28,925 pounds Landed: Concrete runway 33 at Kennedy Space Center, Landed: Concrete runway 33 at Kennedy Space Center, Landed: Concrete runway 33 at Kennedy Space Center, Florida Florida Florida Payloads: Spacehab 01, retrieval of European Retriev- Payloads: Spacehab 01, retrieval of European Retriev- Payloads: Spacehab 01, retrieval of European Retriev- able Carrier (EURECA) Satellite, Superfluid Helium able Carrier (EURECA) Satellite, Superfluid Helium able Carrier (EURECA) Satellite, Superfluid Helium On-Orbit Transfer (SHOOT), Consortium for Mate- On-Orbit Transfer (SHOOT), Consortium for Mate- On-Orbit Transfer (SHOOT), Consortium for Mate- rials Development in Space Complex Autonomous rials Development in Space Complex Autonomous rials Development in Space Complex Autonomous Payload (CONCAP)-IV, Fluid Acquisition and Re- Payload (CONCAP)-IV, Fluid Acquisition and Re- Payload (CONCAP)-IV, Fluid Acquisition and Re- supply Experiment (FARE), Shuttle Amateur Radio supply Experiment (FARE), Shuttle Amateur Radio supply Experiment (FARE), Shuttle Amateur Radio Experiment (SAREX) II, Air Force Maui Optical Site Experiment (SAREX) II, Air Force Maui Optical Site Experiment (SAREX) II, Air Force Maui Optical Site (AMOS), GAS bridge assembly with 12 getaway (AMOS), GAS bridge assembly with 12 getaway (AMOS), GAS bridge assembly with 12 getaway special payloads special payloads special payloads Extravehicular Activity (EVA): G. David Low and Peter Extravehicular Activity (EVA): G. David Low and Peter Extravehicular Activity (EVA): G. David Low and Peter J.K. “Jeff” Wisoff, 5 hours, 50 minutes duration. J.K. “Jeff” Wisoff, 5 hours, 50 minutes duration. J.K. “Jeff” Wisoff, 5 hours, 50 minutes duration. During the EVA, Low and Wisoff conducted tests During the EVA, Low and Wisoff conducted tests During the EVA, Low and Wisoff conducted tests to refine procedures being developed to service to refine procedures being developed to service to refine procedures being developed to service the Hubble Space Telescope and to prepare for the Hubble Space Telescope and to prepare for the Hubble Space Telescope and to prepare for construction of the Space Station. construction of the Space Station. construction of the Space Station. Y-43 Y-43 Y-43 STS-51 Mission Facts — Discovery — STS-51 Mission Facts — Discovery — STS-51 Mission Facts — Discovery — September 12–22, 1993 September 12–22, 1993 September 12–22, 1993

Commander: Frank L. Culbertson, Jr. Commander: Frank L. Culbertson, Jr. Commander: Frank L. Culbertson, Jr. Pilot: William F. Readdy Pilot: William F. Readdy Pilot: William F. Readdy Mission Specialist 1: James H. Newman Mission Specialist 1: James H. Newman Mission Specialist 1: James H. Newman Mission Specialist 2: Daniel W. Bursch Mission Specialist 2: Daniel W. Bursch Mission Specialist 2: Daniel W. Bursch Mission Specialist 3: Carl E. Walz Mission Specialist 3: Carl E. Walz Mission Specialist 3: Carl E. Walz Mission Duration: 216 hours (9 days), 20 hours, Mission Duration: 216 hours (9 days), 20 hours, Mission Duration: 216 hours (9 days), 20 hours, 11 minutes, 11 seconds 11 minutes, 11 seconds 11 minutes, 11 seconds Miles Traveled: Approximately 4,106,411 statute miles Miles Traveled: Approximately 4,106,411 statute miles Miles Traveled: Approximately 4,106,411 statute miles Inclination: 28.45 degrees Inclination: 28.45 degrees Inclination: 28.45 degrees Orbits of Earth: 158 Orbits of Earth: 158 Orbits of Earth: 158 Orbital Altitude: 160 nautical miles (185 statute miles) Orbital Altitude: 160 nautical miles (185 statute miles) Orbital Altitude: 160 nautical miles (185 statute miles) circular orbit circular orbit circular orbit Landing Touchdown: Approximately 2,099 feet beyond Landing Touchdown: Approximately 2,099 feet beyond Landing Touchdown: Approximately 2,099 feet beyond threshold threshold threshold Landing Rollout: Approximately 8,271 feet Landing Rollout: Approximately 8,271 feet Landing Rollout: Approximately 8,271 feet Orbiter Weight at Landing: Approximately 206,438 Orbiter Weight at Landing: Approximately 206,438 Orbiter Weight at Landing: Approximately 206,438 pounds pounds pounds Lift-off Weight: Approximately 4,525,870 pounds Lift-off Weight: Approximately 4,525,870 pounds Lift-off Weight: Approximately 4,525,870 pounds Orbiter Weight at Lift-off: Approximately 261,597 Orbiter Weight at Lift-off: Approximately 261,597 Orbiter Weight at Lift-off: Approximately 261,597 pounds pounds pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 198 knots (228 miles per hour) mately 198 knots (228 miles per hour) mately 198 knots (228 miles per hour) Payload Weight Up: Approximately 42,682 pounds Payload Weight Up: Approximately 42,682 pounds Payload Weight Up: Approximately 42,682 pounds Payload Weight Down: Approximately 8,567 pounds Payload Weight Down: Approximately 8,567 pounds Payload Weight Down: Approximately 8,567 pounds Landed: Concrete runway 15 at Kennedy Space Center, Landed: Concrete runway 15 at Kennedy Space Center, Landed: Concrete runway 15 at Kennedy Space Center, Florida Florida Florida Payloads: Advanced Communication Technology Sat- Payloads: Advanced Communication Technology Sat- Payloads: Advanced Communication Technology Sat- ellite (ACTS)/Transfer Orbit Stage (TOS), Orbiting ellite (ACTS)/Transfer Orbit Stage (TOS), Orbiting ellite (ACTS)/Transfer Orbit Stage (TOS), Orbiting Retrievable Far and Extreme Ultraviolet Retrievable Far and Extreme Ultraviolet Retrievable Far and Extreme Ultraviolet Spectrometer—Shuttle Pallet Satellite Spectrometer—Shuttle Pallet Satellite Spectrometer—Shuttle Pallet Satellite (ORFEUS-SPAS) with Remote IMAX Camera Sys- (ORFEUS-SPAS) with Remote IMAX Camera Sys- (ORFEUS-SPAS) with Remote IMAX Camera Sys- tem (RICS), Limited Duration Space Environ-ment tem (RICS), Limited Duration Space Environ-ment tem (RICS), Limited Duration Space Environ-ment Candidate Materials Exposure (LDCE) (Beam Con- Candidate Materials Exposure (LDCE) (Beam Con- Candidate Materials Exposure (LDCE) (Beam Con- figuration C), Commercial Protein Crystal Growth figuration C), Commercial Protein Crystal Growth figuration C), Commercial Protein Crystal Growth (CPCG—Block II), Chromosome and Plant Cell (CPCG—Block II), Chromosome and Plant Cell (CPCG—Block II), Chromosome and Plant Cell Division in Space (CHROMEX), High Resolution Division in Space (CHROMEX), High Resolution Division in Space (CHROMEX), High Resolution Shuttle Glow Spectroscopy-A (HRSGS-A), Auroral Shuttle Glow Spectroscopy-A (HRSGS-A), Auroral Shuttle Glow Spectroscopy-A (HRSGS-A), Auroral Photography Experiment-B (APE-B), Investigation Photography Experiment-B (APE-B), Investigation Photography Experiment-B (APE-B), Investigation into Polymer Membrane Processing (IPMP), Radia- into Polymer Membrane Processing (IPMP), Radia- into Polymer Membrane Processing (IPMP), Radia- tion Monitoring Equip-ment (RME-III), Air Force tion Monitoring Equip-ment (RME-III), Air Force tion Monitoring Equip-ment (RME-III), Air Force Maui Optical Site Cal-ibration Test (AMOS), IMAX Maui Optical Site Cal-ibration Test (AMOS), IMAX Maui Optical Site Cal-ibration Test (AMOS), IMAX In-Cabin Camera In-Cabin Camera In-Cabin Camera Extravehicular Activity (EVA): Carl E. Walz and James Extravehicular Activity (EVA): Carl E. Walz and James Extravehicular Activity (EVA): Carl E. Walz and James H. Newman, 7 hours, 5 minutes duration. During H. Newman, 7 hours, 5 minutes duration. During H. Newman, 7 hours, 5 minutes duration. During the EVA, Walz and Newman conducted tests in the EVA, Walz and Newman conducted tests in the EVA, Walz and Newman conducted tests in support of the Hubble Space Telescope first ser- support of the Hubble Space Telescope first ser- support of the Hubble Space Telescope first ser- vicing mission and future EVAs, including Space vicing mission and future EVAs, including Space vicing mission and future EVAs, including Space Station assembly and maintenance. Station assembly and maintenance. Station assembly and maintenance.

Y-44 Y-44 Y-44 STS-58 Mission Facts — Columbia — STS-58 Mission Facts — Columbia — STS-58 Mission Facts — Columbia — October 18–November 1, 1993 October 18–November 1, 1993 October 18–November 1, 1993

Commander: John E. Blaha Commander: John E. Blaha Commander: John E. Blaha Pilot: Richard A. Searfoss Pilot: Richard A. Searfoss Pilot: Richard A. Searfoss Payload Commander: M. Rhea Seddon Payload Commander: M. Rhea Seddon Payload Commander: M. Rhea Seddon Mission Specialist: Shannon W. Lucid Mission Specialist: Shannon W. Lucid Mission Specialist: Shannon W. Lucid Mission Specialist: David A. Wolf Mission Specialist: David A. Wolf Mission Specialist: David A. Wolf Mission Specialist: William S. McArthur, Jr. Mission Specialist: William S. McArthur, Jr. Mission Specialist: William S. McArthur, Jr. Payload Specialist: Dr. Martin J. Fettman Payload Specialist: Dr. Martin J. Fettman Payload Specialist: Dr. Martin J. Fettman Mission Duration: 336 hours (14 days), 0 hours, Mission Duration: 336 hours (14 days), 0 hours, Mission Duration: 336 hours (14 days), 0 hours, 12 minutes, 32 seconds 12 minutes, 32 seconds 12 minutes, 32 seconds Miles Traveled: Approximately 5,840,450 statute miles Miles Traveled: Approximately 5,840,450 statute miles Miles Traveled: Approximately 5,840,450 statute miles Inclination: 39 degrees Inclination: 39 degrees Inclination: 39 degrees Orbits of Earth: 225 Orbits of Earth: 225 Orbits of Earth: 225 Orbital Altitude: 153 nautical miles (176 statute miles) Orbital Altitude: 153 nautical miles (176 statute miles) Orbital Altitude: 153 nautical miles (176 statute miles) circular orbit circular orbit circular orbit Landing Touchdown: Approximately 3,380 feet beyond Landing Touchdown: Approximately 3,380 feet beyond Landing Touchdown: Approximately 3,380 feet beyond threshold threshold threshold Landing Rollout: Approximately 9,640 feet Landing Rollout: Approximately 9,640 feet Landing Rollout: Approximately 9,640 feet Orbiter Weight at Landing: Approximately 229,753 Orbiter Weight at Landing: Approximately 229,753 Orbiter Weight at Landing: Approximately 229,753 pounds pounds pounds Lift-off Weight: Approximately 4,519,968 pounds Lift-off Weight: Approximately 4,519,968 pounds Lift-off Weight: Approximately 4,519,968 pounds Orbiter Weight at Lift-off: Approximately 256,007 Orbiter Weight at Lift-off: Approximately 256,007 Orbiter Weight at Lift-off: Approximately 256,007 pounds pounds pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 205 knots (236 miles per hour) mately 205 knots (236 miles per hour) mately 205 knots (236 miles per hour) Payload Weight Up: Approximately 23,188 pounds Payload Weight Up: Approximately 23,188 pounds Payload Weight Up: Approximately 23,188 pounds Payload Weight Down: Approximately 23,188 pounds Payload Weight Down: Approximately 23,188 pounds Payload Weight Down: Approximately 23,188 pounds Landed: Concrete runway 22 at Edwards Air Force Landed: Concrete runway 22 at Edwards Air Force Landed: Concrete runway 22 at Edwards Air Force Base, California Base, California Base, California Payloads: Spacelab Life Sciences (SLS) 2, Shuttle Payloads: Spacelab Life Sciences (SLS) 2, Shuttle Payloads: Spacelab Life Sciences (SLS) 2, Shuttle Amateur Radio Experiment (SAREX) II Amateur Radio Experiment (SAREX) II Amateur Radio Experiment (SAREX) II

STS-61 Mission Facts — Endeavour — STS-61 Mission Facts — Endeavour — STS-61 Mission Facts — Endeavour — December 2–13, 1993 December 2–13, 1993 December 2–13, 1993

Commander: Richard O. Covey Commander: Richard O. Covey Commander: Richard O. Covey Pilot: Kenneth Bowersox Pilot: Kenneth Bowersox Pilot: Kenneth Bowersox Payload Commander: F. Story Musgrave Payload Commander: F. Story Musgrave Payload Commander: F. Story Musgrave Mission Specialist: Thomas D. Akers Mission Specialist: Thomas D. Akers Mission Specialist: Thomas D. Akers Mission Specialist: Jeffrey A. Hoffman Mission Specialist: Jeffrey A. Hoffman Mission Specialist: Jeffrey A. Hoffman Mission Specialist: Kathryn C. Thornton Mission Specialist: Kathryn C. Thornton Mission Specialist: Kathryn C. Thornton Mission Specialist: Claude Nicollier, European Space Mission Specialist: Claude Nicollier, European Space Mission Specialist: Claude Nicollier, European Space Agency Agency Agency Mission Duration: 240 hours (10 days), 19 hours, Mission Duration: 240 hours (10 days), 19 hours, Mission Duration: 240 hours (10 days), 19 hours, 58 minutes, 33 seconds 58 minutes, 33 seconds 58 minutes, 33 seconds Miles Traveled: Approximately 4,433,772 statute miles Miles Traveled: Approximately 4,433,772 statute miles Miles Traveled: Approximately 4,433,772 statute miles Inclination: 28.45 degrees Inclination: 28.45 degrees Inclination: 28.45 degrees Orbits of Earth: 163 Orbits of Earth: 163 Orbits of Earth: 163 Orbital Altitude: 311 nautical miles (358 statute miles) Orbital Altitude: 311 nautical miles (358 statute miles) Orbital Altitude: 311 nautical miles (358 statute miles) Landing Touchdown: Approximately 2,903 feet beyond Landing Touchdown: Approximately 2,903 feet beyond Landing Touchdown: Approximately 2,903 feet beyond threshold threshold threshold

Y-45 Y-45 Y-45 STS-61 Mission Facts (Cont) STS-61 Mission Facts (Cont) STS-61 Mission Facts (Cont)

Landing Rollout: Approximately 7,922 feet Landing Rollout: Approximately 7,922 feet Landing Rollout: Approximately 7,922 feet Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately 211,210 pounds 211,210 pounds 211,210 pounds Lift-off Weight: Approximately 4,515,150 pounds Lift-off Weight: Approximately 4,515,150 pounds Lift-off Weight: Approximately 4,515,150 pounds Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately 250,314 pounds 250,314 pounds 250,314 pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 192 knots (221 miles per hour) mately 192 knots (221 miles per hour) mately 192 knots (221 miles per hour) Payload Weight Up: Approximately 17,662 pounds Payload Weight Up: Approximately 17,662 pounds Payload Weight Up: Approximately 17,662 pounds Payload Weight Down: Approximately 17,662 pounds Payload Weight Down: Approximately 17,662 pounds Payload Weight Down: Approximately 17,662 pounds Landed: Concrete runway 33 at Kennedy Space Center, Landed: Concrete runway 33 at Kennedy Space Center, Landed: Concrete runway 33 at Kennedy Space Center, Florida Florida Florida Payloads: Hubble Space Telescope (HST) Servic- Payloads: Hubble Space Telescope (HST) Servic- Payloads: Hubble Space Telescope (HST) Servic- ing Mission (SM) 1, IMAX Camera, IMAX Cargo ing Mission (SM) 1, IMAX Camera, IMAX Cargo ing Mission (SM) 1, IMAX Camera, IMAX Cargo Bay Camera (ICBC), Air Force Maui Optical Site Bay Camera (ICBC), Air Force Maui Optical Site Bay Camera (ICBC), Air Force Maui Optical Site (AMOS) (AMOS) (AMOS) Extravehicular Activity (EVA): EVA No. 1, F. Story Extravehicular Activity (EVA): EVA No. 1, F. Story Extravehicular Activity (EVA): EVA No. 1, F. Story Musgrave and Jeffrey A. Hoffman, 7 hours, 54 Musgrave and Jeffrey A. Hoffman, 7 hours, 54 Musgrave and Jeffrey A. Hoffman, 7 hours, 54 minutes duration; EVA No. 2, Thomas D. Akers minutes duration; EVA No. 2, Thomas D. Akers minutes duration; EVA No. 2, Thomas D. Akers and Kathryn C. Thornton, 6 hours, 36 minutes and Kathryn C. Thornton, 6 hours, 36 minutes and Kathryn C. Thornton, 6 hours, 36 minutes duration; EVA No. 3, F. Story Musgrave and Jeffrey duration; EVA No. 3, F. Story Musgrave and Jeffrey duration; EVA No. 3, F. Story Musgrave and Jeffrey A. Hoffman, 6 hours, 47 minutes duration; EVA A. Hoffman, 6 hours, 47 minutes duration; EVA A. Hoffman, 6 hours, 47 minutes duration; EVA No. 4, Thomas D. Akers and Kathryn C. Thornton, No. 4, Thomas D. Akers and Kathryn C. Thornton, No. 4, Thomas D. Akers and Kathryn C. Thornton, 6 hours, 50 minutes duration; EVA No. 5, F. Story 6 hours, 50 minutes duration; EVA No. 5, F. Story 6 hours, 50 minutes duration; EVA No. 5, F. Story Musgrave and Jeffrey A. Hoffman, 7 hours, 21 Musgrave and Jeffrey A. Hoffman, 7 hours, 21 Musgrave and Jeffrey A. Hoffman, 7 hours, 21 minutes duration. During EVA 1, Musgrave and minutes duration. During EVA 1, Musgrave and minutes duration. During EVA 1, Musgrave and Hoffman successfully changed out Hubble’s rate Hoffman successfully changed out Hubble’s rate Hoffman successfully changed out Hubble’s rate sensing units and electronics control unit and sensing units and electronics control unit and sensing units and electronics control unit and eight fuse plugs. The spacewalk was the second eight fuse plugs. The spacewalk was the second eight fuse plugs. The spacewalk was the second longest in NASA history. During EVA 2, Akers longest in NASA history. During EVA 2, Akers longest in NASA history. During EVA 2, Akers and Thornton installed two new solar arrays and and Thornton installed two new solar arrays and and Thornton installed two new solar arrays and jettisoned one of Hubble’s original solar arrays, jettisoned one of Hubble’s original solar arrays, jettisoned one of Hubble’s original solar arrays, which was bent. During EVA 3, Musgrave and which was bent. During EVA 3, Musgrave and which was bent. During EVA 3, Musgrave and Hoffman removed and stored the telescope’s origi- Hoffman removed and stored the telescope’s origi- Hoffman removed and stored the telescope’s origi- nal wide-field/planetary camera and installed the nal wide-field/planetary camera and installed the nal wide-field/planetary camera and installed the replacement Wide-Field/Planetary Camera II and replacement Wide-Field/Planetary Camera II and replacement Wide-Field/Planetary Camera II and two new magnetometers. During EVA 4, Akers two new magnetometers. During EVA 4, Akers two new magnetometers. During EVA 4, Akers and Thornton removed the telescope’s high-speed and Thornton removed the telescope’s high-speed and Thornton removed the telescope’s high-speed photometer and installed the corrective optics photometer and installed the corrective optics photometer and installed the corrective optics space telescope axial replacement unit and a new space telescope axial replacement unit and a new space telescope axial replacement unit and a new computer coprocessor. Akers broke the all-time computer coprocessor. Akers broke the all-time computer coprocessor. Akers broke the all-time American spacewalking record previously set by American spacewalking record previously set by American spacewalking record previously set by Eugene Cernan, accumulating a total of 29 hours Eugene Cernan, accumulating a total of 29 hours Eugene Cernan, accumulating a total of 29 hours and 40 minutes. During EVA 5, Musgrave and and 40 minutes. During EVA 5, Musgrave and and 40 minutes. During EVA 5, Musgrave and Hoffman replaced the telescope’s solar array drive Hoffman replaced the telescope’s solar array drive Hoffman replaced the telescope’s solar array drive electronics and installed the Goddard high-resolu- electronics and installed the Goddard high-resolu- electronics and installed the Goddard high-resolu- tion spectrograph redundancy kit and two Mylar tion spectrograph redundancy kit and two Mylar tion spectrograph redundancy kit and two Mylar covers over the original magnetometers to contain covers over the original magnetometers to contain covers over the original magnetometers to contain any contamination or debris that might come any contamination or debris that might come any contamination or debris that might come off the instrument and protect it from ultraviolet off the instrument and protect it from ultraviolet off the instrument and protect it from ultraviolet degradation. degradation. degradation. Most EVAs on a Space Shuttle Flight: 5 Most EVAs on a Space Shuttle Flight: 5 Most EVAs on a Space Shuttle Flight: 5

Y-46 Y-46 Y-46 STS-60 Mission Facts — Discovery — STS-60 Mission Facts — Discovery — STS-60 Mission Facts — Discovery — February 3–11, 1994 February 3–11, 1994 February 3–11, 1994

Commander: Charles F. Bolden, Jr. Commander: Charles F. Bolden, Jr. Commander: Charles F. Bolden, Jr. Pilot: Kenneth S. Reightler, Jr. Pilot: Kenneth S. Reightler, Jr. Pilot: Kenneth S. Reightler, Jr. Mission Specialist: Franklin R. Chang-Diaz Mission Specialist: Franklin R. Chang-Diaz Mission Specialist: Franklin R. Chang-Diaz Mission Specialist: N. Jan Davis Mission Specialist: N. Jan Davis Mission Specialist: N. Jan Davis Mission Specialist: Ronald M. Sega Mission Specialist: Ronald M. Sega Mission Specialist: Ronald M. Sega Mission Specialist: Sergei K. Krikalev, Russian Mission Specialist: Sergei K. Krikalev, Russian Mission Specialist: Sergei K. Krikalev, Russian cosmonaut cosmonaut cosmonaut Mission Duration: 192 hours (8 days), 7 hours, Mission Duration: 192 hours (8 days), 7 hours, Mission Duration: 192 hours (8 days), 7 hours, 10 minutes, 13 seconds 10 minutes, 13 seconds 10 minutes, 13 seconds Miles Traveled: Approximately 3,439,704 statute miles Miles Traveled: Approximately 3,439,704 statute miles Miles Traveled: Approximately 3,439,704 statute miles Inclination: 57 degrees Inclination: 57 degrees Inclination: 57 degrees Orbits of Earth: 131 Orbits of Earth: 131 Orbits of Earth: 131 Orbital Altitude: 190 nautical miles (219 statute miles) Orbital Altitude: 190 nautical miles (219 statute miles) Orbital Altitude: 190 nautical miles (219 statute miles) Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 192 knots (221 miles per hour) mately 192 knots (221 miles per hour) mately 192 knots (221 miles per hour) Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately 214,944 pounds 214,944 pounds 214,944 pounds Lift-off Weight: Approximately 4,508,352 pounds Lift-off Weight: Approximately 4,508,352 pounds Lift-off Weight: Approximately 4,508,352 pounds Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately 245,278 pounds 245,278 pounds 245,278 pounds Landing Touchdown: Approximately 2,380 feet beyond Landing Touchdown: Approximately 2,380 feet beyond Landing Touchdown: Approximately 2,380 feet beyond threshold threshold threshold Landing Rollout: Approximately 10,144 feet Landing Rollout: Approximately 10,144 feet Landing Rollout: Approximately 10,144 feet Payload Weight Up: Approximately 28,674 pounds Payload Weight Up: Approximately 28,674 pounds Payload Weight Up: Approximately 28,674 pounds Payload Weight Down: Approximately 28,499 pounds Payload Weight Down: Approximately 28,499 pounds Payload Weight Down: Approximately 28,499 pounds Landed: Concrete runway 33 at Kennedy Space Center, Landed: Concrete runway 33 at Kennedy Space Center, Landed: Concrete runway 33 at Kennedy Space Center, Florida Florida Florida Payloads: Wake Shield Facility (WSF) 1 and SPACEHAB Payloads: Wake Shield Facility (WSF) 1 and SPACEHAB Payloads: Wake Shield Facility (WSF) 1 and SPACEHAB 02. Getaway special bridge assembly experi- 02. Getaway special bridge assembly experi- 02. Getaway special bridge assembly experi- ments: Capillary Pumped Loop (CAPL), Orbital ments: Capillary Pumped Loop (CAPL), Orbital ments: Capillary Pumped Loop (CAPL), Orbital Debris Radar Calibration Spheres (ODERACS), Debris Radar Calibration Spheres (ODERACS), Debris Radar Calibration Spheres (ODERACS), University of Bremen Satellite (BREMSAT), G-514, University of Bremen Satellite (BREMSAT), G-514, University of Bremen Satellite (BREMSAT), G-514, G-071, and G-536. Shuttle Amateur Radio Experi- G-071, and G-536. Shuttle Amateur Radio Experi- G-071, and G-536. Shuttle Amateur Radio Experi- ment (SAREX) II; Auroral Photography Experiment ment (SAREX) II; Auroral Photography Experiment ment (SAREX) II; Auroral Photography Experiment (APE-B) (APE-B) (APE-B)

STS-62 Mission Facts — Columbia — STS-62 Mission Facts — Columbia — STS-62 Mission Facts — Columbia — March 4–18, 1994 March 4–18, 1994 March 4–18, 1994

Commander: John H. Casper Commander: John H. Casper Commander: John H. Casper Pilot: Andrew M. Allen Pilot: Andrew M. Allen Pilot: Andrew M. Allen Mission Specialist: Pierre J. Thuot Mission Specialist: Pierre J. Thuot Mission Specialist: Pierre J. Thuot Mission Specialist: Charles D. “Sam” Gemar Mission Specialist: Charles D. “Sam” Gemar Mission Specialist: Charles D. “Sam” Gemar Mission Specialist: Marsha S. Ivins Mission Specialist: Marsha S. Ivins Mission Specialist: Marsha S. Ivins Mission Duration: 312 hours (13 days), 23 hours, Mission Duration: 312 hours (13 days), 23 hours, Mission Duration: 312 hours (13 days), 23 hours, 17 minutes, 28 seconds 17 minutes, 28 seconds 17 minutes, 28 seconds Miles Traveled: Approximately 5,820,146 statute miles Miles Traveled: Approximately 5,820,146 statute miles Miles Traveled: Approximately 5,820,146 statute miles Inclination: 39 degrees Inclination: 39 degrees Inclination: 39 degrees Orbits of Earth: 224 Orbits of Earth: 224 Orbits of Earth: 224 Orbital Altitude: 160 nautical miles (184 statute miles) Orbital Altitude: 160 nautical miles (184 statute miles) Orbital Altitude: 160 nautical miles (184 statute miles)

Y-47 Y-47 Y-47 STS-62 Mission Facts (Cont) STS-62 Mission Facts (Cont) STS-62 Mission Facts (Cont)

Landing Touchdown: Approximately 2,905 feet beyond Landing Touchdown: Approximately 2,905 feet beyond Landing Touchdown: Approximately 2,905 feet beyond threshold threshold threshold Landing Rollout: Approximately 10,166 feet Landing Rollout: Approximately 10,166 feet Landing Rollout: Approximately 10,166 feet Orbiter Weight at Landing: Approximately 226,742 Orbiter Weight at Landing: Approximately 226,742 Orbiter Weight at Landing: Approximately 226,742 pounds pounds pounds Lift-off Weight: Approximately 4,519,308 pounds Lift-off Weight: Approximately 4,519,308 pounds Lift-off Weight: Approximately 4,519,308 pounds Orbiter Weight at Lift-off: Approximately 256,086 Orbiter Weight at Lift-off: Approximately 256,086 Orbiter Weight at Lift-off: Approximately 256,086 pounds pounds pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 211 knots (242 miles per hour) mately 211 knots (242 miles per hour) mately 211 knots (242 miles per hour) Payload Weight Up: Approximately 19,556 pounds Payload Weight Up: Approximately 19,556 pounds Payload Weight Up: Approximately 19,556 pounds Payload Weight Down: Approximately 19,556 pounds Payload Weight Down: Approximately 19,556 pounds Payload Weight Down: Approximately 19,556 pounds Landed: Concrete runway 33 at Kennedy Space Center, Landed: Concrete runway 33 at Kennedy Space Center, Landed: Concrete runway 33 at Kennedy Space Center, Florida Florida Florida Payloads: United States Microgravity Payload (USMP) Payloads: United States Microgravity Payload (USMP) Payloads: United States Microgravity Payload (USMP) 2, Office of Aeronautics and Space Technology 2, Office of Aeronautics and Space Technology 2, Office of Aeronautics and Space Technology (OAST) 2, Dexterous End Effector (DEE), Shuttle (OAST) 2, Dexterous End Effector (DEE), Shuttle (OAST) 2, Dexterous End Effector (DEE), Shuttle Solar Backscatter Ultraviolet/A (SSBUV/A), Lim- Solar Backscatter Ultraviolet/A (SSBUV/A), Lim- Solar Backscatter Ultraviolet/A (SSBUV/A), Lim- ited-Duration Space Environment Candidate Mate- ited-Duration Space Environment Candidate Mate- ited-Duration Space Environment Candidate Mate- rial Exposure (LDCE), Advanced Protein Crystal rial Exposure (LDCE), Advanced Protein Crystal rial Exposure (LDCE), Advanced Protein Crystal Growth (APCG), Physiological Systems Experi- Growth (APCG), Physiological Systems Experi- Growth (APCG), Physiological Systems Experi- ment (PSE), Commercial Protein Crystal Growth ment (PSE), Commercial Protein Crystal Growth ment (PSE), Commercial Protein Crystal Growth (CPCG), Commercial Generic Bioprocessing Ap- (CPCG), Commercial Generic Bioprocessing Ap- (CPCG), Commercial Generic Bioprocessing Ap- paratus (CGBA), Auroral Photography Experiment paratus (CGBA), Auroral Photography Experiment paratus (CGBA), Auroral Photography Experiment Phase B (APE-B), Middeck Zero-Gravity Dynamics Phase B (APE-B), Middeck Zero-Gravity Dynamics Phase B (APE-B), Middeck Zero-Gravity Dynamics Experiment (MODE), Air Force Maui Optical Site Experiment (MODE), Air Force Maui Optical Site Experiment (MODE), Air Force Maui Optical Site (AMOS) Calibration Test, Bioreactor Demonstra- (AMOS) Calibration Test, Bioreactor Demonstra- (AMOS) Calibration Test, Bioreactor Demonstra- tion System A. tion System A. tion System A.

STS-59 Mission Facts — Endeavour — STS-59 Mission Facts — Endeavour — STS-59 Mission Facts — Endeavour — April 9–20, 1994 April 9–20, 1994 April 9–20, 1994

Commander: Sidney M. Gutierrez Commander: Sidney M. Gutierrez Commander: Sidney M. Gutierrez Pilot: Kevin P. Chilton Pilot: Kevin P. Chilton Pilot: Kevin P. Chilton Payload Commander: Linda M. Godwin Payload Commander: Linda M. Godwin Payload Commander: Linda M. Godwin Mission Specialist: Jay Apt Mission Specialist: Jay Apt Mission Specialist: Jay Apt Mission Specialist: Michael R. “Rich” Clifford Mission Specialist: Michael R. “Rich” Clifford Mission Specialist: Michael R. “Rich” Clifford Mission Specialist: Thomas D. Jones Mission Specialist: Thomas D. Jones Mission Specialist: Thomas D. Jones Mission Duration: 264 hours (11 days), 5 hours, Mission Duration: 264 hours (11 days), 5 hours, Mission Duration: 264 hours (11 days), 5 hours, 49 minutes, 30 seconds 49 minutes, 30 seconds 49 minutes, 30 seconds Miles Traveled: Approximately 4,704,835 statute miles Miles Traveled: Approximately 4,704,835 statute miles Miles Traveled: Approximately 4,704,835 statute miles Inclination: 57 degrees Inclination: 57 degrees Inclination: 57 degrees Orbits of Earth: 183 Orbits of Earth: 183 Orbits of Earth: 183 Orbital Altitude: 120 nautical miles (138 statute miles) Orbital Altitude: 120 nautical miles (138 statute miles) Orbital Altitude: 120 nautical miles (138 statute miles) Landing Touchdown: Approximately 1,619 feet beyond Landing Touchdown: Approximately 1,619 feet beyond Landing Touchdown: Approximately 1,619 feet beyond threshold threshold threshold Landing Rollout: Approximately 10,636 feet Landing Rollout: Approximately 10,636 feet Landing Rollout: Approximately 10,636 feet Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately 221,713 pounds 221,713 pounds 221,713 pounds Lift-off Weight: Approximately 4,510,987 pounds Lift-off Weight: Approximately 4,510,987 pounds Lift-off Weight: Approximately 4,510,987 pounds

Y-48 Y-48 Y-48 STS-59 Mission Facts (Cont) STS-59 Mission Facts (Cont) STS-59 Mission Facts (Cont)

Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately 246,575 pounds 246,575 pounds 246,575 pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 228 knots (262 miles per hour) mately 228 knots (262 miles per hour) mately 228 knots (262 miles per hour) Payload Weight Up: Approximately 27,536 pounds Payload Weight Up: Approximately 27,536 pounds Payload Weight Up: Approximately 27,536 pounds Payload Weight Down: Approximately 27,536 pounds Payload Weight Down: Approximately 27,536 pounds Payload Weight Down: Approximately 27,536 pounds Landed: Concrete runway 22 at Edwards Air Force Landed: Concrete runway 22 at Edwards Air Force Landed: Concrete runway 22 at Edwards Air Force Base, California Base, California Base, California Payloads: Space Radar Laboratory (SRL) 1; Consortium Payloads: Space Radar Laboratory (SRL) 1; Consortium Payloads: Space Radar Laboratory (SRL) 1; Consortium for Materials Development in Space Com-plex for Materials Development in Space Com-plex for Materials Development in Space Com-plex Autonomous Payload (CONCAP) IV; three getaway Autonomous Payload (CONCAP) IV; three getaway Autonomous Payload (CONCAP) IV; three getaway special (GAS) payloads; Space Tissue Loss (STL) special (GAS) payloads; Space Tissue Loss (STL) special (GAS) payloads; Space Tissue Loss (STL) A, B; Visual Function Tester (VFT) 4; Shuttle Ama- A, B; Visual Function Tester (VFT) 4; Shuttle Ama- A, B; Visual Function Tester (VFT) 4; Shuttle Ama- teur Radio Experiment (SAREX) II teur Radio Experiment (SAREX) II teur Radio Experiment (SAREX) II

STS-65 Mission Facts — Columbia — STS-65 Mission Facts — Columbia — STS-65 Mission Facts — Columbia — July 8–23, 1994 July 8–23, 1994 July 8–23, 1994

Commander: Robert D. Cabana Commander: Robert D. Cabana Commander: Robert D. Cabana Pilot: James D. Halsell, Jr. Pilot: James D. Halsell, Jr. Pilot: James D. Halsell, Jr. Payload Commander: Richard J. Hieb Payload Commander: Richard J. Hieb Payload Commander: Richard J. Hieb Mission Specialist: Carl E. Walz Mission Specialist: Carl E. Walz Mission Specialist: Carl E. Walz Mission Specialist: Leroy Chiao Mission Specialist: Leroy Chiao Mission Specialist: Leroy Chiao Mission Specialist: Donald A. Thomas Mission Specialist: Donald A. Thomas Mission Specialist: Donald A. Thomas Payload Specialist: Chiaki Mukai, Japan Payload Specialist: Chiaki Mukai, Japan Payload Specialist: Chiaki Mukai, Japan Mission Duration: 336 hours (14 days), 17 hours, Mission Duration: 336 hours (14 days), 17 hours, Mission Duration: 336 hours (14 days), 17 hours, 56 minutes 56 minutes 56 minutes Miles Traveled: Approximately 6,100,000 statute miles Miles Traveled: Approximately 6,100,000 statute miles Miles Traveled: Approximately 6,100,000 statute miles Inclination: 28.45 degrees Inclination: 28.45 degrees Inclination: 28.45 degrees Orbits of Earth: 236 Orbits of Earth: 236 Orbits of Earth: 236 Orbital Altitude: 160 nautical miles (184 statute miles) Orbital Altitude: 160 nautical miles (184 statute miles) Orbital Altitude: 160 nautical miles (184 statute miles) Landing Touchdown: Approximately 2,996 feet beyond Landing Touchdown: Approximately 2,996 feet beyond Landing Touchdown: Approximately 2,996 feet beyond threshold threshold threshold Landing Rollout: Approximately 10,211 feet Landing Rollout: Approximately 10,211 feet Landing Rollout: Approximately 10,211 feet Orbiter Weight at Landing: Approximately 229,522 Orbiter Weight at Landing: Approximately 229,522 Orbiter Weight at Landing: Approximately 229,522 pounds pounds pounds Lift-off Weight: Approximately 4,522,475 pounds Lift-off Weight: Approximately 4,522,475 pounds Lift-off Weight: Approximately 4,522,475 pounds Orbiter Weight at Lift-off: Approximately 258,333 Orbiter Weight at Lift-off: Approximately 258,333 Orbiter Weight at Lift-off: Approximately 258,333 pounds pounds pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 207 knots ( 238 miles per hour) mately 207 knots ( 238 miles per hour) mately 207 knots ( 238 miles per hour) Payload Weight Up: Approximately 23,836 pounds Payload Weight Up: Approximately 23,836 pounds Payload Weight Up: Approximately 23,836 pounds Payload Weight Down: Approximately 23,836 pounds Payload Weight Down: Approximately 23,836 pounds Payload Weight Down: Approximately 23,836 pounds Landed: Concrete runway 33 at Kennedy Space Center, Landed: Concrete runway 33 at Kennedy Space Center, Landed: Concrete runway 33 at Kennedy Space Center, Florida Florida Florida Payloads: International Microgravity Laboratory (IML) 2, Payloads: International Microgravity Laboratory (IML) 2, Payloads: International Microgravity Laboratory (IML) 2, Orbital Acceleration Research Experiment (OARE), Orbital Acceleration Research Experiment (OARE), Orbital Acceleration Research Experiment (OARE), Commercial Protein Crystal Growth (CPCG), Air Commercial Protein Crystal Growth (CPCG), Air Commercial Protein Crystal Growth (CPCG), Air Force Maui Optical Site (AMOS), Military Appli- Force Maui Optical Site (AMOS), Military Appli- Force Maui Optical Site (AMOS), Military Appli- cations of Ship Tracks (MAST), Shuttle Amateur cations of Ship Tracks (MAST), Shuttle Amateur cations of Ship Tracks (MAST), Shuttle Amateur Radio Experiment (SAREX) Radio Experiment (SAREX) Radio Experiment (SAREX)

Y-49 Y-49 Y-49 STS-64 Mission Facts — Discovery — STS-64 Mission Facts — Discovery — STS-64 Mission Facts — Discovery — September 9–20, 1994 September 9–20, 1994 September 9–20, 1994

Commander: Richard N. Richards Commander: Richard N. Richards Commander: Richard N. Richards Pilot: L. Blaine Hammond, Jr. Pilot: L. Blaine Hammond, Jr. Pilot: L. Blaine Hammond, Jr. Mission Specialist: Carl J. Meade Mission Specialist: Carl J. Meade Mission Specialist: Carl J. Meade Mission Specialist: Mark C.Lee Mission Specialist: Mark C.Lee Mission Specialist: Mark C.Lee Mission Specialist: Susan J. Helms Mission Specialist: Susan J. Helms Mission Specialist: Susan J. Helms Mission Specialist: Jerry M. Linenger Mission Specialist: Jerry M. Linenger Mission Specialist: Jerry M. Linenger Mission Duration: 240 hours (10 days), 22 hours, Mission Duration: 240 hours (10 days), 22 hours, Mission Duration: 240 hours (10 days), 22 hours, 49 minutes, 57 seconds 49 minutes, 57 seconds 49 minutes, 57 seconds Miles Traveled: Approximately 4,576,174 statute miles Miles Traveled: Approximately 4,576,174 statute miles Miles Traveled: Approximately 4,576,174 statute miles Inclination: 57 degrees Inclination: 57 degrees Inclination: 57 degrees Orbits of Earth: 177 Orbits of Earth: 177 Orbits of Earth: 177 Orbital Altitude: 140 nautical miles (161 statute miles) Orbital Altitude: 140 nautical miles (161 statute miles) Orbital Altitude: 140 nautical miles (161 statute miles) Landing Touchdown: Approximately 3,386 feet beyond Landing Touchdown: Approximately 3,386 feet beyond Landing Touchdown: Approximately 3,386 feet beyond threshold threshold threshold Landing Rollout: Approximately 9,656 feet Landing Rollout: Approximately 9,656 feet Landing Rollout: Approximately 9,656 feet Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately 212,056 pounds 212,056 pounds 212,056 pounds Lift-off Weight: Approximately 4,504,154 pounds Lift-off Weight: Approximately 4,504,154 pounds Lift-off Weight: Approximately 4,504,154 pounds Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately 242,768 pounds 242,768 pounds 242,768 pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 207.8 knots (239 miles per hour) mately 207.8 knots (239 miles per hour) mately 207.8 knots (239 miles per hour) Payload Weight Up: Approximately 20,417 pounds Payload Weight Up: Approximately 20,417 pounds Payload Weight Up: Approximately 20,417 pounds Payload Weight Down: Approximately 20,375 pounds Payload Weight Down: Approximately 20,375 pounds Payload Weight Down: Approximately 20,375 pounds Landed: Concrete runway 04 at Edwards Air Force Landed: Concrete runway 04 at Edwards Air Force Landed: Concrete runway 04 at Edwards Air Force Base, California Base, California Base, California Payloads: Lidar In-Space Technology Experiment Payloads: Lidar In-Space Technology Experiment Payloads: Lidar In-Space Technology Experiment (LITE), Shuttle Pointed Autonomous Research Tool (LITE), Shuttle Pointed Autonomous Research Tool (LITE), Shuttle Pointed Autonomous Research Tool for Astronomy (SPARTAN) 201-II, Robot-Operated for Astronomy (SPARTAN) 201-II, Robot-Operated for Astronomy (SPARTAN) 201-II, Robot-Operated Materials Processing System (ROMPS), Shuttle Materials Processing System (ROMPS), Shuttle Materials Processing System (ROMPS), Shuttle Plume Impingement Flight Experiment (SPIFEX), Plume Impingement Flight Experiment (SPIFEX), Plume Impingement Flight Experiment (SPIFEX), getaway special (GAS) bridge assembly with getaway special (GAS) bridge assembly with getaway special (GAS) bridge assembly with ten GAS experiments, Trajectory Control Sensor ten GAS experiments, Trajectory Control Sensor ten GAS experiments, Trajectory Control Sensor (TCS), Simplified Aid for EVA Rescue (SAFER), (TCS), Simplified Aid for EVA Rescue (SAFER), (TCS), Simplified Aid for EVA Rescue (SAFER), Solid Surface Combustion Experiment (SSCE), Solid Surface Combustion Experiment (SSCE), Solid Surface Combustion Experiment (SSCE), Biological Research in Canisters (BRIC) III, Radia- Biological Research in Canisters (BRIC) III, Radia- Biological Research in Canisters (BRIC) III, Radia- tion Monitoring Experiment (RME) III, Military Ap- tion Monitoring Experiment (RME) III, Military Ap- tion Monitoring Experiment (RME) III, Military Ap- plications of Ship Tracks (MAST), Shuttle Amateur plications of Ship Tracks (MAST), Shuttle Amateur plications of Ship Tracks (MAST), Shuttle Amateur Radio Experiment (SAREX) II, Air Force Maui Radio Experiment (SAREX) II, Air Force Maui Radio Experiment (SAREX) II, Air Force Maui Optical Site (AMOS) Calibration Test Optical Site (AMOS) Calibration Test Optical Site (AMOS) Calibration Test Extravehicular Activity (EVA): Mark C. Lee and Carl J. Extravehicular Activity (EVA): Mark C. Lee and Carl J. Extravehicular Activity (EVA): Mark C. Lee and Carl J. Meade, for 6 hours, 51 minutes. Lee and Meade, for 6 hours, 51 minutes. Lee and Meade, for 6 hours, 51 minutes. Lee and Meade tested the Simplified Aid for EVA Res- Meade tested the Simplified Aid for EVA Res- Meade tested the Simplified Aid for EVA Res- cue (SAFER), a small, self-contained propulsive cue (SAFER), a small, self-contained propulsive cue (SAFER), a small, self-contained propulsive backpack device that provides free-flying mobility backpack device that provides free-flying mobility backpack device that provides free-flying mobility for an EVA astronaut in an emergency. They for an EVA astronaut in an emergency. They for an EVA astronaut in an emergency. They also evaluated several tools and an electronic also evaluated several tools and an electronic also evaluated several tools and an electronic cuff checklist that allows crew members greater cuff checklist that allows crew members greater cuff checklist that allows crew members greater and easier access to information away from the and easier access to information away from the and easier access to information away from the spacecraft. spacecraft. spacecraft.

Y-50 Y-50 Y-50 STS-68 Mission Facts — Endeavour — STS-68 Mission Facts — Endeavour — STS-68 Mission Facts — Endeavour — September 30–October 11, 1994 September 30–October 11, 1994 September 30–October 11, 1994

Commander: Michael A. Baker Commander: Michael A. Baker Commander: Michael A. Baker Pilot: Terrence W. Wilcutt Pilot: Terrence W. Wilcutt Pilot: Terrence W. Wilcutt Payload Commander: Thomas David Jones Payload Commander: Thomas David Jones Payload Commander: Thomas David Jones Mission Specialist: Steven L. Smith Mission Specialist: Steven L. Smith Mission Specialist: Steven L. Smith Mission Specialist: Peter J.K. “Jeff” Wisoff Mission Specialist: Peter J.K. “Jeff” Wisoff Mission Specialist: Peter J.K. “Jeff” Wisoff Mission Specialist: Daniel W. Bursch Mission Specialist: Daniel W. Bursch Mission Specialist: Daniel W. Bursch Mission Duration: 264 hours (11 days), 5 hours, Mission Duration: 264 hours (11 days), 5 hours, Mission Duration: 264 hours (11 days), 5 hours, 47 minutes, 8 seconds 47 minutes, 8 seconds 47 minutes, 8 seconds Miles Traveled: Approximately 4,703,000 statute miles Miles Traveled: Approximately 4,703,000 statute miles Miles Traveled: Approximately 4,703,000 statute miles Inclination: 57 degrees Inclination: 57 degrees Inclination: 57 degrees Orbits of Earth: 183 Orbits of Earth: 183 Orbits of Earth: 183 Orbital Altitude: 120 nautical miles (138 statute miles) Orbital Altitude: 120 nautical miles (138 statute miles) Orbital Altitude: 120 nautical miles (138 statute miles) circular orbit circular orbit circular orbit Landing Touchdown: Approximately 3,522 feet beyond Landing Touchdown: Approximately 3,522 feet beyond Landing Touchdown: Approximately 3,522 feet beyond threshold threshold threshold Landing Rollout: Approximately 8,495 feet Landing Rollout: Approximately 8,495 feet Landing Rollout: Approximately 8,495 feet Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately 222,026 pounds 222,026 pounds 222,026 pounds Lift-off Weight: Approximately 4,510,392 pounds Lift-off Weight: Approximately 4,510,392 pounds Lift-off Weight: Approximately 4,510,392 pounds Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately 247,129 pounds 247,129 pounds 247,129 pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 230 knots (265 miles per hour) mately 230 knots (265 miles per hour) mately 230 knots (265 miles per hour) Payload Weight Up: Approximately 27,582 pounds Payload Weight Up: Approximately 27,582 pounds Payload Weight Up: Approximately 27,582 pounds Payload Weight Down: Approximately 27,582 pounds Payload Weight Down: Approximately 27,582 pounds Payload Weight Down: Approximately 27,582 pounds Landed: Concrete runway 22 at Edwards Air Force Landed: Concrete runway 22 at Edwards Air Force Landed: Concrete runway 22 at Edwards Air Force Base, California Base, California Base, California Payloads: Space Radar Laboratory (SRL) 2, five Get- Payloads: Space Radar Laboratory (SRL) 2, five Get- Payloads: Space Radar Laboratory (SRL) 2, five Get- away Special payloads, Chromosome and Plant away Special payloads, Chromosome and Plant away Special payloads, Chromosome and Plant Cell Division in Space (CHROMEX) 5, Biological Cell Division in Space (CHROMEX) 5, Biological Cell Division in Space (CHROMEX) 5, Biological Research in Canisters (BRIC) 01, Cosmic Radia- Research in Canisters (BRIC) 01, Cosmic Radia- Research in Canisters (BRIC) 01, Cosmic Radia- tion Effects and Activation Monitor (CREAM), tion Effects and Activation Monitor (CREAM), tion Effects and Activation Monitor (CREAM), Military Application of Ship Tracks (MAST), Com- Military Application of Ship Tracks (MAST), Com- Military Application of Ship Tracks (MAST), Com- mercial Protein Crystal Growth (CPCG) mercial Protein Crystal Growth (CPCG) mercial Protein Crystal Growth (CPCG)

STS-66 Mission Facts — Atlantis — STS-66 Mission Facts — Atlantis — STS-66 Mission Facts — Atlantis — November 3–14, 1994 November 3–14, 1994 November 3–14, 1994

Commander: Donald R. McMonagle Commander: Donald R. McMonagle Commander: Donald R. McMonagle Pilot: Curtis L. Brown, Jr. Pilot: Curtis L. Brown, Jr. Pilot: Curtis L. Brown, Jr. Payload Commander: Ellen Ochoa Payload Commander: Ellen Ochoa Payload Commander: Ellen Ochoa Mission Specialist: Scott E. Parazynski Mission Specialist: Scott E. Parazynski Mission Specialist: Scott E. Parazynski Mission Specialist: Joseph R. Tanner Mission Specialist: Joseph R. Tanner Mission Specialist: Joseph R. Tanner Mission Specialist: Jean-Francois Clervoy, European Mission Specialist: Jean-Francois Clervoy, European Mission Specialist: Jean-Francois Clervoy, European Space Agency Space Agency Space Agency Mission Duration: 240 hours (10 days), Mission Duration: 240 hours (10 days), Mission Duration: 240 hours (10 days), 22 hours, 34 minutes, 51 seconds 22 hours, 34 minutes, 51 seconds 22 hours, 34 minutes, 51 seconds Miles Traveled: Approximately 4,554,791 Miles Traveled: Approximately 4,554,791 Miles Traveled: Approximately 4,554,791 statute miles statute miles statute miles Inclination: 57 degrees Inclination: 57 degrees Inclination: 57 degrees

Y-51 Y-51 Y-51 STS-66 Mission Facts (Cont) STS-66 Mission Facts (Cont) STS-66 Mission Facts (Cont)

Orbits of Earth: 174 Orbits of Earth: 174 Orbits of Earth: 174 Orbital Altitude: 164 nautical miles (189 statute miles) Orbital Altitude: 164 nautical miles (189 statute miles) Orbital Altitude: 164 nautical miles (189 statute miles) Landing Touchdown: Approximately 3,219 feet beyond Landing Touchdown: Approximately 3,219 feet beyond Landing Touchdown: Approximately 3,219 feet beyond threshold threshold threshold Landing Rollout: Approximately 7,647 feet Landing Rollout: Approximately 7,647 feet Landing Rollout: Approximately 7,647 feet Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately 209,842 pounds 209,842 pounds 209,842 pounds Lift-off Weight: Approximately 4,508,369 pounds Lift-off Weight: Approximately 4,508,369 pounds Lift-off Weight: Approximately 4,508,369 pounds Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately 243,839 pounds 243,839 pounds 243,839 pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 196 knots (226 miles per hour) mately 196 knots (226 miles per hour) mately 196 knots (226 miles per hour) Payload Weight Up: Approximately 23,247 pounds Payload Weight Up: Approximately 23,247 pounds Payload Weight Up: Approximately 23,247 pounds Payload Weight Down: Approximately 23,247 pounds Payload Weight Down: Approximately 23,247 pounds Payload Weight Down: Approximately 23,247 pounds Landed: Concrete runway 22 at Edwards Air Force Landed: Concrete runway 22 at Edwards Air Force Landed: Concrete runway 22 at Edwards Air Force Base, California Base, California Base, California Payloads: Atmospheric Laboratory for Applications and Payloads: Atmospheric Laboratory for Applications and Payloads: Atmospheric Laboratory for Applications and Science (ATLAS) 3, Cryogenic Infrared Spectrome- Science (ATLAS) 3, Cryogenic Infrared Spectrome- Science (ATLAS) 3, Cryogenic Infrared Spectrome- ters and Telescopes for the Atmosphere (CRISTA)- ters and Telescopes for the Atmosphere (CRISTA)- ters and Telescopes for the Atmosphere (CRISTA)- Shuttle Pallet Satellite (SPAS) 1, Experiment of the Shuttle Pallet Satellite (SPAS) 1, Experiment of the Shuttle Pallet Satellite (SPAS) 1, Experiment of the Sun for Complementing the ATLAS Payload for Sun for Complementing the ATLAS Payload for Sun for Complementing the ATLAS Payload for Education (ESCAPE) II, Inter-Mars Tissue Equiva- Education (ESCAPE) II, Inter-Mars Tissue Equiva- Education (ESCAPE) II, Inter-Mars Tissue Equiva- lent Proportional Counter (ITEPC), Shuttle Solar lent Proportional Counter (ITEPC), Shuttle Solar lent Proportional Counter (ITEPC), Shuttle Solar Backscatter Ultraviolet (SSBUV) A, Physiological Backscatter Ultraviolet (SSBUV) A, Physiological Backscatter Ultraviolet (SSBUV) A, Physiological and Anatomical Rodent Experiment (PARE/NIH-R), and Anatomical Rodent Experiment (PARE/NIH-R), and Anatomical Rodent Experiment (PARE/NIH-R), Protein Crystal Growth (PCG-TES and PCG-STES), Protein Crystal Growth (PCG-TES and PCG-STES), Protein Crystal Growth (PCG-TES and PCG-STES), Space Tissue Loss (STL/NIH-C-A), Shuttle Accel- Space Tissue Loss (STL/NIH-C-A), Shuttle Accel- Space Tissue Loss (STL/NIH-C-A), Shuttle Accel- eration Measurement System (SAMS), Heat Pipe eration Measurement System (SAMS), Heat Pipe eration Measurement System (SAMS), Heat Pipe Performance (HPP) Performance (HPP) Performance (HPP)

STS-63 Mission Facts — Discovery — STS-63 Mission Facts — Discovery — STS-63 Mission Facts — Discovery — February 3–11, 1995 February 3–11, 1995 February 3–11, 1995

Commander: James D. Wetherbee Commander: James D. Wetherbee Commander: James D. Wetherbee Pilot: Eileen Marie Collins Pilot: Eileen Marie Collins Pilot: Eileen Marie Collins Mission Specialist: C. Michael Foale Mission Specialist: C. Michael Foale Mission Specialist: C. Michael Foale Mission Specialist: Janice E. Voss Mission Specialist: Janice E. Voss Mission Specialist: Janice E. Voss Mission Specialist: Bernard A. Harris, Jr. Mission Specialist: Bernard A. Harris, Jr. Mission Specialist: Bernard A. Harris, Jr. Mission Specialist: Vladimir Titov, Russian Space Mission Specialist: Vladimir Titov, Russian Space Mission Specialist: Vladimir Titov, Russian Space Agency Agency Agency Mission Duration: 192 hours (8 days), 6 hours, Mission Duration: 192 hours (8 days), 6 hours, Mission Duration: 192 hours (8 days), 6 hours, 29 minutes, 35 seconds 29 minutes, 35 seconds 29 minutes, 35 seconds Miles Traveled: Approximately 2,992,806 Miles Traveled: Approximately 2,992,806 Miles Traveled: Approximately 2,992,806 statute miles statute miles statute miles Inclination: 51.6 degrees Inclination: 51.6 degrees Inclination: 51.6 degrees Orbits of Earth: 130 Orbits of Earth: 130 Orbits of Earth: 130 Orbital Altitude: 170-213 nautical miles Orbital Altitude: 170-213 nautical miles Orbital Altitude: 170-213 nautical miles (196-245 statute miles) (196-245 statute miles) (196-245 statute miles) Landing Touchdown: Approximately 1,261 feet Landing Touchdown: Approximately 1,261 feet Landing Touchdown: Approximately 1,261 feet beyond threshold beyond threshold beyond threshold

Y-52 Y-52 Y-52 STS-63 Mission Facts (Cont) STS-63 Mission Facts (Cont) STS-63 Mission Facts (Cont)

Landing Rollout: Approximately 11,008 feet Landing Rollout: Approximately 11,008 feet Landing Rollout: Approximately 11,008 feet Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately 211,278 pounds 211,278 pounds 211,278 pounds Lift-off Weight: Approximately 4,511,481 pounds Lift-off Weight: Approximately 4,511,481 pounds Lift-off Weight: Approximately 4,511,481 pounds Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately 247,476 pounds 247,476 pounds 247,476 pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 206 knots (237 miles per hour) mately 206 knots (237 miles per hour) mately 206 knots (237 miles per hour) Payload Weight Up: Approximately 19,051 pounds Payload Weight Up: Approximately 19,051 pounds Payload Weight Up: Approximately 19,051 pounds Payload Weight Down: Approximately 18,994 pounds Payload Weight Down: Approximately 18,994 pounds Payload Weight Down: Approximately 18,994 pounds Landed: Concrete runway 15 at Kennedy Space Center, Landed: Concrete runway 15 at Kennedy Space Center, Landed: Concrete runway 15 at Kennedy Space Center, Florida Florida Florida Payloads: SPACEHAB 03, Shuttle Pointed Autonomous Payloads: SPACEHAB 03, Shuttle Pointed Autonomous Payloads: SPACEHAB 03, Shuttle Pointed Autonomous Research Tool for Astronomy (SPARTAN) 204, Research Tool for Astronomy (SPARTAN) 204, Research Tool for Astronomy (SPARTAN) 204, Cryo Systems Experiment (CSE)/GLO-2 Experi- Cryo Systems Experiment (CSE)/GLO-2 Experi- Cryo Systems Experiment (CSE)/GLO-2 Experi- ment Payload (CGP)/Orbital Debris Radar Calibra- ment Payload (CGP)/Orbital Debris Radar Calibra- ment Payload (CGP)/Orbital Debris Radar Calibra- tion Spheres (ODERACS) 2, Solid Surface Com- tion Spheres (ODERACS) 2, Solid Surface Com- tion Spheres (ODERACS) 2, Solid Surface Com- bustion Experiment (SSCE), Air Force Maui Optical bustion Experiment (SSCE), Air Force Maui Optical bustion Experiment (SSCE), Air Force Maui Optical Site (AMOS), IMAX Cargo Bay Camera (ICBC) Site (AMOS), IMAX Cargo Bay Camera (ICBC) Site (AMOS), IMAX Cargo Bay Camera (ICBC) Note: Discovery rendezvoused with Russia’s space Note: Discovery rendezvoused with Russia’s space Note: Discovery rendezvoused with Russia’s space station, Mir, to a distance of 37 feet and performed station, Mir, to a distance of 37 feet and performed station, Mir, to a distance of 37 feet and performed a fly-around. a fly-around. a fly-around. Extravehicular Activity (EVA): Bernard A. Harris, Jr., Extravehicular Activity (EVA): Bernard A. Harris, Jr., Extravehicular Activity (EVA): Bernard A. Harris, Jr., and C. Michael Foale, for 4 hours, 39 minutes. and C. Michael Foale, for 4 hours, 39 minutes. and C. Michael Foale, for 4 hours, 39 minutes. Harris and Foale evaluated spacesuit Harris and Foale evaluated spacesuit Harris and Foale evaluated spacesuit modifications that would provide astronauts with modifications that would provide astronauts with modifications that would provide astronauts with better thermal protection from cold and practiced better thermal protection from cold and practiced better thermal protection from cold and practiced handling large objects in space in order to handling large objects in space in order to handling large objects in space in order to increase NASA's experience base as it prepares increase NASA's experience base as it prepares increase NASA's experience base as it prepares for the on-orbit assembly of the international space for the on-orbit assembly of the international space for the on-orbit assembly of the international space station. The EVA was terminated prematurely when station. The EVA was terminated prematurely when station. The EVA was terminated prematurely when Harris and Foale reported they were getting too Harris and Foale reported they were getting too Harris and Foale reported they were getting too cold. cold. cold.

STS-67 Mission Facts — Endeavour — STS-67 Mission Facts — Endeavour — STS-67 Mission Facts — Endeavour — March 2–18, 1995 March 2–18, 1995 March 2–18, 1995

Commander: Stephen S. Oswald Commander: Stephen S. Oswald Commander: Stephen S. Oswald Pilot: William G. Gregory Pilot: William G. Gregory Pilot: William G. Gregory Payload Commander: Tamara E. Jernigan Payload Commander: Tamara E. Jernigan Payload Commander: Tamara E. Jernigan Mission Specialist: John M. Grunsfeld Mission Specialist: John M. Grunsfeld Mission Specialist: John M. Grunsfeld Mission Specialist: Wendy B. Lawrence Mission Specialist: Wendy B. Lawrence Mission Specialist: Wendy B. Lawrence Payload Specialist: Ronald A. Parise Payload Specialist: Ronald A. Parise Payload Specialist: Ronald A. Parise Payload Specialist: Samuel T. Durrance Payload Specialist: Samuel T. Durrance Payload Specialist: Samuel T. Durrance Mission Duration: 384 hours (16 days), 15 hours, Mission Duration: 384 hours (16 days), 15 hours, Mission Duration: 384 hours (16 days), 15 hours, 9 minutes, 46 seconds 9 minutes, 46 seconds 9 minutes, 46 seconds Miles Traveled: Approximately 6,900,000 statute miles Miles Traveled: Approximately 6,900,000 statute miles Miles Traveled: Approximately 6,900,000 statute miles Inclination: 28.45 degrees Inclination: 28.45 degrees Inclination: 28.45 degrees Orbits of Earth: 263 Orbits of Earth: 263 Orbits of Earth: 263 Orbital Altitude: 190 nautical miles (219 statute miles) Orbital Altitude: 190 nautical miles (219 statute miles) Orbital Altitude: 190 nautical miles (219 statute miles)

Y-53 Y-53 Y-53 STS-67 Mission Facts (Cont) STS-67 Mission Facts (Cont) STS-67 Mission Facts (Cont)

Landing Touchdown: Approximately 1,672 feet beyond Landing Touchdown: Approximately 1,672 feet beyond Landing Touchdown: Approximately 1,672 feet beyond threshold threshold threshold Landing Rollout: Approximately 9,975 feet Landing Rollout: Approximately 9,975 feet Landing Rollout: Approximately 9,975 feet Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately 217,989 pounds 217,989 pounds 217,989 pounds Lift-off Weight: Approximately 4,520,785 pounds Lift-off Weight: Approximately 4,520,785 pounds Lift-off Weight: Approximately 4,520,785 pounds Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately 256,293 pounds 256,293 pounds 256,293 pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 201 knots (231 miles per hour) mately 201 knots (231 miles per hour) mately 201 knots (231 miles per hour) Payload Weight Up: Approximately 28,916 pounds Payload Weight Up: Approximately 28,916 pounds Payload Weight Up: Approximately 28,916 pounds Payload Weight Down: Approximately 28,916 pounds Payload Weight Down: Approximately 28,916 pounds Payload Weight Down: Approximately 28,916 pounds Landed: Concrete runway 22 at Edwards Air Force Landed: Concrete runway 22 at Edwards Air Force Landed: Concrete runway 22 at Edwards Air Force Base, California Base, California Base, California Payloads: Ultraviolet Astronomy (ASTRO) 2; Mid- Payloads: Ultraviolet Astronomy (ASTRO) 2; Mid- Payloads: Ultraviolet Astronomy (ASTRO) 2; Mid- deck Active Control Experiment (MACE); Protein deck Active Control Experiment (MACE); Protein deck Active Control Experiment (MACE); Protein Crystal Growth—Thermal Enclosure System Crystal Growth—Thermal Enclosure System Crystal Growth—Thermal Enclosure System (PCG-TES) 03; Protein Crystal Growth—Single- (PCG-TES) 03; Protein Crystal Growth—Single- (PCG-TES) 03; Protein Crystal Growth—Single- Locker Thermal Enclosure System (PCG-STES) Locker Thermal Enclosure System (PCG-STES) Locker Thermal Enclosure System (PCG-STES) 02; Commercial Materials Dispersion Apparatus 02; Commercial Materials Dispersion Apparatus 02; Commercial Materials Dispersion Apparatus Minilab/Instrumentation Technology Associates, Minilab/Instrumentation Technology Associates, Minilab/Instrumentation Technology Associates, Inc. Experiments (CMIX) 03; Shuttle Amateur Inc. Experiments (CMIX) 03; Shuttle Amateur Inc. Experiments (CMIX) 03; Shuttle Amateur Radio Experiment (SAREX) II; two getaway special Radio Experiment (SAREX) II; two getaway special Radio Experiment (SAREX) II; two getaway special experiments experiments experiments

STS-71 Mission Facts — Atlantis — STS-71 Mission Facts — Atlantis — STS-71 Mission Facts — Atlantis — June 27–July 7, 1995 June 27–July 7, 1995 June 27–July 7, 1995

Commander: Robert L. “Hoot” Gibson Commander: Robert L. “Hoot” Gibson Commander: Robert L. “Hoot” Gibson Pilot: Charles J. Precourt, Jr. Pilot: Charles J. Precourt, Jr. Pilot: Charles J. Precourt, Jr. Mission Specialist: Ellen S. Baker Mission Specialist: Ellen S. Baker Mission Specialist: Ellen S. Baker Mission Specialist: Gregory J. Harbaugh Mission Specialist: Gregory J. Harbaugh Mission Specialist: Gregory J. Harbaugh Mission Specialist: Bonnie J. Dunbar Mission Specialist: Bonnie J. Dunbar Mission Specialist: Bonnie J. Dunbar Mir-19 Crew Member: Anatoly Solovyez (Russia)— Mir-19 Crew Member: Anatoly Solovyez (Russia)— Mir-19 Crew Member: Anatoly Solovyez (Russia)— up only up only up only Mir-19 Crew Member: Nikolai Budarin (Russia)— Mir-19 Crew Member: Nikolai Budarin (Russia)— Mir-19 Crew Member: Nikolai Budarin (Russia)— up only up only up only Mir-18 Crew Member: Vladimir Dezhurov (Russia)— Mir-18 Crew Member: Vladimir Dezhurov (Russia)— Mir-18 Crew Member: Vladimir Dezhurov (Russia)— down only down only down only Mir-18 Crew Member: Gennadiy Strekalov (Russia)— Mir-18 Crew Member: Gennadiy Strekalov (Russia)— Mir-18 Crew Member: Gennadiy Strekalov (Russia)— down only down only down only Mir-18 Crew Member: Norman E. Thagard (U.S.)— Mir-18 Crew Member: Norman E. Thagard (U.S.)— Mir-18 Crew Member: Norman E. Thagard (U.S.)— down only down only down only Mission Duration: 216 hours (9 days), 19 hours, Mission Duration: 216 hours (9 days), 19 hours, Mission Duration: 216 hours (9 days), 19 hours, 23 minutes, 8 seconds 23 minutes, 8 seconds 23 minutes, 8 seconds Miles Traveled: Approximately 4,100,000 statute Miles Traveled: Approximately 4,100,000 statute Miles Traveled: Approximately 4,100,000 statute miles miles miles Inclination: 51.6 degrees Inclination: 51.6 degrees Inclination: 51.6 degrees Orbits of Earth: 154 Orbits of Earth: 154 Orbits of Earth: 154 Orbital Altitude: 213 nautical miles (245 statute miles) Orbital Altitude: 213 nautical miles (245 statute miles) Orbital Altitude: 213 nautical miles (245 statute miles) Landing Touchdown: Approximately 2,324 feet beyond Landing Touchdown: Approximately 2,324 feet beyond Landing Touchdown: Approximately 2,324 feet beyond threshold threshold threshold

Y-54 Y-54 Y-54 STS-71 Mission Facts (Cont) STS-71 Mission Facts (Cont) STS-71 Mission Facts (Cont)

Landing Rollout: Approximately 8,353 feet Landing Rollout: Approximately 8,353 feet Landing Rollout: Approximately 8,353 feet Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately 214,709 pounds 214,709 pounds 214,709 pounds Lift-off Weight: Approximately 4,511,483 pounds Lift-off Weight: Approximately 4,511,483 pounds Lift-off Weight: Approximately 4,511,483 pounds Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately 248,417 pounds 248,417 pounds 248,417 pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 206 knots (237 miles per hour) mately 206 knots (237 miles per hour) mately 206 knots (237 miles per hour) Payload Weight Up: Approximately 26,878 pounds Payload Weight Up: Approximately 26,878 pounds Payload Weight Up: Approximately 26,878 pounds Payload Weight Down: Approximately 27,410 pounds Payload Weight Down: Approximately 27,410 pounds Payload Weight Down: Approximately 27,410 pounds Landed: Concrete runway 15 at Kennedy Space Center, Landed: Concrete runway 15 at Kennedy Space Center, Landed: Concrete runway 15 at Kennedy Space Center, Florida Florida Florida Payloads: Shuttle/Mir Mission 1, Spacelab-Mir, IMAX Payloads: Shuttle/Mir Mission 1, Spacelab-Mir, IMAX Payloads: Shuttle/Mir Mission 1, Spacelab-Mir, IMAX camera, Shuttle Amateur Radio Experiment camera, Shuttle Amateur Radio Experiment camera, Shuttle Amateur Radio Experiment (SAREX) (SAREX) (SAREX)

STS-70 Mission Facts — Discovery — STS-70 Mission Facts — Discovery — STS-70 Mission Facts — Discovery — July 13–22, 1995 July 13–22, 1995 July 13–22, 1995

Commander: Terrence T. Henricks Commander: Terrence T. Henricks Commander: Terrence T. Henricks Pilot: Kevin R. Kregel Pilot: Kevin R. Kregel Pilot: Kevin R. Kregel Mission Specialist: Nancy J. Currie Mission Specialist: Nancy J. Currie Mission Specialist: Nancy J. Currie Mission Specialist: Donald A. Thomas Mission Specialist: Donald A. Thomas Mission Specialist: Donald A. Thomas Mission Specialist: Mary Ellen Weber Mission Specialist: Mary Ellen Weber Mission Specialist: Mary Ellen Weber Mission Duration: 192 hours (8 days), Mission Duration: 192 hours (8 days), Mission Duration: 192 hours (8 days), 22 hours, 20 minutes, 5 seconds 22 hours, 20 minutes, 5 seconds 22 hours, 20 minutes, 5 seconds Miles Traveled: Approximately Miles Traveled: Approximately Miles Traveled: Approximately 3,700,000 statute miles 3,700,000 statute miles 3,700,000 statute miles Inclination: 28.45 degrees Inclination: 28.45 degrees Inclination: 28.45 degrees Orbits of Earth: 142 Orbits of Earth: 142 Orbits of Earth: 142 Orbital Altitude: 160 nautical miles Orbital Altitude: 160 nautical miles Orbital Altitude: 160 nautical miles (184 statute miles) (184 statute miles) (184 statute miles) Landing Touchdown: Approximately 2,696 feet beyond Landing Touchdown: Approximately 2,696 feet beyond Landing Touchdown: Approximately 2,696 feet beyond threshold threshold threshold Landing Rollout: Approximately 8,472 feet Landing Rollout: Approximately 8,472 feet Landing Rollout: Approximately 8,472 feet Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately 194,911 pounds 194,911 pounds 194,911 pounds Lift-off Weight: Approximately 4,521,772 pounds Lift-off Weight: Approximately 4,521,772 pounds Lift-off Weight: Approximately 4,521,772 pounds Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately 258,584 pounds 258,584 pounds 258,584 pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 199 knots (229 miles per hour) mately 199 knots (229 miles per hour) mately 199 knots (229 miles per hour) Payload Weight Up: Approximately 44,445 pounds Payload Weight Up: Approximately 44,445 pounds Payload Weight Up: Approximately 44,445 pounds Payload Weight Down: Approximately 6,671 pounds Payload Weight Down: Approximately 6,671 pounds Payload Weight Down: Approximately 6,671 pounds Landed: Concrete runway 33 at Kennedy Space Center, Landed: Concrete runway 33 at Kennedy Space Center, Landed: Concrete runway 33 at Kennedy Space Center, Florida Florida Florida

Y-55 Y-55 Y-55 STS-70 Mission Facts (Cont) STS-70 Mission Facts (Cont) STS-70 Mission Facts (Cont)

Payloads: Tracking and Data Relay Satellite (TDRS) Payloads: Tracking and Data Relay Satellite (TDRS) Payloads: Tracking and Data Relay Satellite (TDRS) G/Inertial Upper Stage (IUS); Bioreactor Dem- G/Inertial Upper Stage (IUS); Bioreactor Dem- G/Inertial Upper Stage (IUS); Bioreactor Dem- onstration System (BDS) B; Biological Research onstration System (BDS) B; Biological Research onstration System (BDS) B; Biological Research in Canisters (BRIC); Commercial Protein Crystal in Canisters (BRIC); Commercial Protein Crystal in Canisters (BRIC); Commercial Protein Crystal Growth (CPCG); Hand-Held, Earth-Oriented, Real- Growth (CPCG); Hand-Held, Earth-Oriented, Real- Growth (CPCG); Hand-Held, Earth-Oriented, Real- Time, Cooperative, User-Friendly, Location-Target- Time, Cooperative, User-Friendly, Location-Target- Time, Cooperative, User-Friendly, Location-Target- ing and Environmental System (HERCULES); Mi- ing and Environmental System (HERCULES); Mi- ing and Environmental System (HERCULES); Mi- crocapsules in Space (MIS) B; Physiological and crocapsules in Space (MIS) B; Physiological and crocapsules in Space (MIS) B; Physiological and Anatomical Rodent Experiment (PARE)/National Anatomical Rodent Experiment (PARE)/National Anatomical Rodent Experiment (PARE)/National Institutes of Health (NIH) Rodents (R); Radiation Institutes of Health (NIH) Rodents (R); Radiation Institutes of Health (NIH) Rodents (R); Radiation Monitoring Experiment (RME) III; Shuttle Amateur Monitoring Experiment (RME) III; Shuttle Amateur Monitoring Experiment (RME) III; Shuttle Amateur Radio Experiment (SAREX) II; Space Tissue Loss Radio Experiment (SAREX) II; Space Tissue Loss Radio Experiment (SAREX) II; Space Tissue Loss (STL)/National Institutes of Health (NIH) Cells (C); (STL)/National Institutes of Health (NIH) Cells (C); (STL)/National Institutes of Health (NIH) Cells (C); Military Applications of Ship Tracks (MAST); Visual Military Applications of Ship Tracks (MAST); Visual Military Applications of Ship Tracks (MAST); Visual Function Tester (VFT) 4; Window Experiment Function Tester (VFT) 4; Window Experiment Function Tester (VFT) 4; Window Experiment (WINDEX) (WINDEX) (WINDEX)

STS-69 Mission Facts — Endeavour — STS-69 Mission Facts — Endeavour — STS-69 Mission Facts — Endeavour — September 7–18, 1995 September 7–18, 1995 September 7–18, 1995

Commander: David M. Walker Commander: David M. Walker Commander: David M. Walker Pilot: Kenneth D. Cockrell Pilot: Kenneth D. Cockrell Pilot: Kenneth D. Cockrell Payload Commander: James S. Voss Payload Commander: James S. Voss Payload Commander: James S. Voss Mission Specialist: James H. Newman Mission Specialist: James H. Newman Mission Specialist: James H. Newman Mission Specialist: Michael L. Gernhardt Mission Specialist: Michael L. Gernhardt Mission Specialist: Michael L. Gernhardt Mission Duration: 240 hours (10 days), 20 hours, Mission Duration: 240 hours (10 days), 20 hours, Mission Duration: 240 hours (10 days), 20 hours, 29 minutes, 52 seconds 29 minutes, 52 seconds 29 minutes, 52 seconds Miles Traveled: Approximately 4,500,000 statute miles Miles Traveled: Approximately 4,500,000 statute miles Miles Traveled: Approximately 4,500,000 statute miles Inclination: 28.45 degrees Inclination: 28.45 degrees Inclination: 28.45 degrees Orbits of Earth: 171 Orbits of Earth: 171 Orbits of Earth: 171 Orbital Altitude: 200 nautical miles (230 statute miles) Orbital Altitude: 200 nautical miles (230 statute miles) Orbital Altitude: 200 nautical miles (230 statute miles) Landing Touchdown: Approximately 1,912 feet beyond Landing Touchdown: Approximately 1,912 feet beyond Landing Touchdown: Approximately 1,912 feet beyond threshold threshold threshold Landing Rollout: Approximately 10,230 feet Landing Rollout: Approximately 10,230 feet Landing Rollout: Approximately 10,230 feet Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately 219,887 pounds 219,887 pounds 219,887 pounds Lift-off Weight: Approximately 4,520,139 pounds Lift-off Weight: Approximately 4,520,139 pounds Lift-off Weight: Approximately 4,520,139 pounds Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately 256,808 pounds 256,808 pounds 256,808 pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 218 knots (251 miles per hour) mately 218 knots (251 miles per hour) mately 218 knots (251 miles per hour) Payload Weight Up: Approximately 25,352 pounds Payload Weight Up: Approximately 25,352 pounds Payload Weight Up: Approximately 25,352 pounds Payload Weight Down: Approximately 25,304 pounds Payload Weight Down: Approximately 25,304 pounds Payload Weight Down: Approximately 25,304 pounds Landed: Concrete runway 33 at Kennedy Space Center, Landed: Concrete runway 33 at Kennedy Space Center, Landed: Concrete runway 33 at Kennedy Space Center, Florida Florida Florida Payloads: Wake Shield Facility (WSF) 2; Shuttle Payloads: Wake Shield Facility (WSF) 2; Shuttle Payloads: Wake Shield Facility (WSF) 2; Shuttle Pointed Autonomous Research Tool for Pointed Autonomous Research Tool for Pointed Autonomous Research Tool for Astronomy (SPARTAN) 201; International Extreme Astronomy (SPARTAN) 201; International Extreme Astronomy (SPARTAN) 201; International Extreme Ultraviolet Hitchhiker (IEH)1; Inter-Mars Tissue Ultraviolet Hitchhiker (IEH)1; Inter-Mars Tissue Ultraviolet Hitchhiker (IEH)1; Inter-Mars Tissue Equivalent Proportional Counter (ITEPC); Equivalent Proportional Counter (ITEPC); Equivalent Proportional Counter (ITEPC); Extravehicular Activity Development Flight Test Extravehicular Activity Development Flight Test Extravehicular Activity Development Flight Test (EDFT) 2; Capillary Pumped Loop (CAPL) 2/ (EDFT) 2; Capillary Pumped Loop (CAPL) 2/ (EDFT) 2; Capillary Pumped Loop (CAPL) 2/

Y-56 Y-56 Y-56 STS-69 Mission Facts (Cont) STS-69 Mission Facts (Cont) STS-69 Mission Facts (Cont) getaway special (GAS) bridge assembly with five getaway special (GAS) bridge assembly with five getaway special (GAS) bridge assembly with five GAS payloads; Auroral Photography Experiment GAS payloads; Auroral Photography Experiment GAS payloads; Auroral Photography Experiment (APE) B; Biological Research in Canisters (BRIC); (APE) B; Biological Research in Canisters (BRIC); (APE) B; Biological Research in Canisters (BRIC); Commercial Generic Bioprocessing Apparatus Commercial Generic Bioprocessing Apparatus Commercial Generic Bioprocessing Apparatus (CGBA), Configuration A; Electrolysis Performance (CGBA), Configuration A; Electrolysis Performance (CGBA), Configuration A; Electrolysis Performance Improvement Concept Study (EPICS); Space Improvement Concept Study (EPICS); Space Improvement Concept Study (EPICS); Space Tissue Loss (STL)/National Institutes of Health Tissue Loss (STL)/National Institutes of Health Tissue Loss (STL)/National Institutes of Health (NIH)—Cells (C); Commercial Middeck Instrumen- (NIH)—Cells (C); Commercial Middeck Instrumen- (NIH)—Cells (C); Commercial Middeck Instrumen- tation Technology Associates Experiment (CMIX) tation Technology Associates Experiment (CMIX) tation Technology Associates Experiment (CMIX) Extravehicular Activity (EVA): James S. Voss and Extravehicular Activity (EVA): James S. Voss and Extravehicular Activity (EVA): James S. Voss and Michael L. Gernhardt for 6 hours, 45 minutes. Michael L. Gernhardt for 6 hours, 45 minutes. Michael L. Gernhardt for 6 hours, 45 minutes. Voss and Gernhardt performed a number of tasks Voss and Gernhardt performed a number of tasks Voss and Gernhardt performed a number of tasks designed to evaluate and verify specific assembly designed to evaluate and verify specific assembly designed to evaluate and verify specific assembly and maintenance techniques and tools for the and maintenance techniques and tools for the and maintenance techniques and tools for the International Space Station. They also evaluated International Space Station. They also evaluated International Space Station. They also evaluated spacesuit design modifications to protect space- spacesuit design modifications to protect space- spacesuit design modifications to protect space- walkers from the extremely cold space environ- walkers from the extremely cold space environ- walkers from the extremely cold space environ- ment as well as an electronic cuff checklist device ment as well as an electronic cuff checklist device ment as well as an electronic cuff checklist device worn on the wrist. worn on the wrist. worn on the wrist. STS-73 Mission Facts — Columbia — STS-73 Mission Facts — Columbia — STS-73 Mission Facts — Columbia — October 20–November 5, 1995 October 20–November 5, 1995 October 20–November 5, 1995

Commander: Kenneth D. Bowersox Commander: Kenneth D. Bowersox Commander: Kenneth D. Bowersox Pilot: Kent V. Rominger Pilot: Kent V. Rominger Pilot: Kent V. Rominger Payload Commander: Kathryn C. Thornton Payload Commander: Kathryn C. Thornton Payload Commander: Kathryn C. Thornton Mission Specialist: Catherine G. “Cady” Coleman Mission Specialist: Catherine G. “Cady” Coleman Mission Specialist: Catherine G. “Cady” Coleman Mission Specialist: Michael E. Lopez-Alegria Mission Specialist: Michael E. Lopez-Alegria Mission Specialist: Michael E. Lopez-Alegria Payload Specialist: Fred W. Leslie Payload Specialist: Fred W. Leslie Payload Specialist: Fred W. Leslie Payload Specialist: Albert Sacco, Jr. Payload Specialist: Albert Sacco, Jr. Payload Specialist: Albert Sacco, Jr. Mission Duration: 360 hours (15 days), 21 hours, Mission Duration: 360 hours (15 days), 21 hours, Mission Duration: 360 hours (15 days), 21 hours, 53 minutes, 16 seconds 53 minutes, 16 seconds 53 minutes, 16 seconds Miles Traveled: Approximately 6.6 million statute miles Miles Traveled: Approximately 6.6 million statute miles Miles Traveled: Approximately 6.6 million statute miles Inclination: 39 degrees Inclination: 39 degrees Inclination: 39 degrees Orbits of Earth: 256 Orbits of Earth: 256 Orbits of Earth: 256 Orbital Altitude: 150 nautical miles (173 statute miles) Orbital Altitude: 150 nautical miles (173 statute miles) Orbital Altitude: 150 nautical miles (173 statute miles) Landing Touchdown: Approximately 2,500 feet beyond Landing Touchdown: Approximately 2,500 feet beyond Landing Touchdown: Approximately 2,500 feet beyond threshold threshold threshold Landing Rollout: Approximately 9,117 feet Landing Rollout: Approximately 9,117 feet Landing Rollout: Approximately 9,117 feet Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately 230,164 pounds 230,164 pounds 230,164 pounds Lift-off Weight: Approximately 4,521,539 pounds Lift-off Weight: Approximately 4,521,539 pounds Lift-off Weight: Approximately 4,521,539 pounds Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately 257,162 pounds 257,162 pounds 257,162 pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 213 knots (245 miles per hour) mately 213 knots (245 miles per hour) mately 213 knots (245 miles per hour) Payload Weight Up: Approximately 33,622 pounds Payload Weight Up: Approximately 33,622 pounds Payload Weight Up: Approximately 33,622 pounds Payload Weight Down: Approximately 33,622 pounds Payload Weight Down: Approximately 33,622 pounds Payload Weight Down: Approximately 33,622 pounds Landed: Concrete runway 33 at Kennedy Space Center, Landed: Concrete runway 33 at Kennedy Space Center, Landed: Concrete runway 33 at Kennedy Space Center, Florida Florida Florida Payloads: United States Microgravity Laboratory Payloads: United States Microgravity Laboratory Payloads: United States Microgravity Laboratory (USML) 2, Orbital Acceleration Research (USML) 2, Orbital Acceleration Research (USML) 2, Orbital Acceleration Research Experiment (OARE) Experiment (OARE) Experiment (OARE)

Y-57 Y-57 Y-57 STS-74 Mission Facts — Atlantis — STS-74 Mission Facts — Atlantis — STS-74 Mission Facts — Atlantis — November 12–20, 1995 November 12–20, 1995 November 12–20, 1995

Commander: Kenneth D. Cameron Commander: Kenneth D. Cameron Commander: Kenneth D. Cameron Pilot: James D. Halsell, Jr. Pilot: James D. Halsell, Jr. Pilot: James D. Halsell, Jr. Mission Specialist 1: Chris A. Hadfield, Canadian Mission Specialist 1: Chris A. Hadfield, Canadian Mission Specialist 1: Chris A. Hadfield, Canadian Space Agency Space Agency Space Agency Mission Specialist 2: Jerry L. Ross Mission Specialist 2: Jerry L. Ross Mission Specialist 2: Jerry L. Ross Mission Specialist 3: William S. McArthur, Jr. Mission Specialist 3: William S. McArthur, Jr. Mission Specialist 3: William S. McArthur, Jr. Mir 20 Crew Members (Aboard Mir): Mir 20 Crew Members (Aboard Mir): Mir 20 Crew Members (Aboard Mir): Commander: Yuri Gidzenko, Russian Space Agency Commander: Yuri Gidzenko, Russian Space Agency Commander: Yuri Gidzenko, Russian Space Agency Flight Engineer: Sergei Avdeyev, Russian Space Flight Engineer: Sergei Avdeyev, Russian Space Flight Engineer: Sergei Avdeyev, Russian Space Agency Agency Agency Cosmonaut-Researcher: Thomas Reiter, European Cosmonaut-Researcher: Thomas Reiter, European Cosmonaut-Researcher: Thomas Reiter, European Space Agency Space Agency Space Agency Mission Duration: 192 hours (8 days), 4 hours, Mission Duration: 192 hours (8 days), 4 hours, Mission Duration: 192 hours (8 days), 4 hours, 31 minutes, 42 seconds 31 minutes, 42 seconds 31 minutes, 42 seconds Miles Traveled: Approximately 3.4 million Miles Traveled: Approximately 3.4 million Miles Traveled: Approximately 3.4 million statute miles statute miles statute miles Inclination: 51.6 degrees Inclination: 51.6 degrees Inclination: 51.6 degrees Orbits of Earth: 129 Orbits of Earth: 129 Orbits of Earth: 129 Orbital Altitude: 160 nautical miles (184 statute miles) Orbital Altitude: 160 nautical miles (184 statute miles) Orbital Altitude: 160 nautical miles (184 statute miles) insertion; 213 nautical miles (245 statute miles) for insertion; 213 nautical miles (245 statute miles) for insertion; 213 nautical miles (245 statute miles) for Mir rendezvous Mir rendezvous Mir rendezvous Landing Touchdown: Approximately 2,471 feet beyond Landing Touchdown: Approximately 2,471 feet beyond Landing Touchdown: Approximately 2,471 feet beyond threshold threshold threshold Landing Rollout: Approximately 8,691 feet Landing Rollout: Approximately 8,691 feet Landing Rollout: Approximately 8,691 feet Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately 204,375 pounds 204,375 pounds 204,375 pounds Lift-off Weight: Approximately 4,511,797 pounds Lift-off Weight: Approximately 4,511,797 pounds Lift-off Weight: Approximately 4,511,797 pounds Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately 247,709 pounds 247,709 pounds 247,709 pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 196 knots (226 miles per hour) mately 196 knots (226 miles per hour) mately 196 knots (226 miles per hour) Payload Weight Up: Approximately 13,525 pounds Payload Weight Up: Approximately 13,525 pounds Payload Weight Up: Approximately 13,525 pounds Payload Weight Down: Approximately 3,938 pounds Payload Weight Down: Approximately 3,938 pounds Payload Weight Down: Approximately 3,938 pounds Landed: Concrete runway 33 at Kennedy Space Center, Landed: Concrete runway 33 at Kennedy Space Center, Landed: Concrete runway 33 at Kennedy Space Center, Florida Florida Florida Payloads: Shuttle-Mir Mission 2; docking module with Payloads: Shuttle-Mir Mission 2; docking module with Payloads: Shuttle-Mir Mission 2; docking module with two attached solar arrays; IMAX Cargo Bay Cam- two attached solar arrays; IMAX Cargo Bay Cam- two attached solar arrays; IMAX Cargo Bay Cam- era (ICBC); Glow Experiment (GLO-4)/ Photogram- era (ICBC); Glow Experiment (GLO-4)/ Photogram- era (ICBC); Glow Experiment (GLO-4)/ Photogram- metric Appendage Structural Dynamics Experi- metric Appendage Structural Dynamics Experi- metric Appendage Structural Dynamics Experi- ment (PASDE) Payload (GPP); Shuttle Amateur ment (PASDE) Payload (GPP); Shuttle Amateur ment (PASDE) Payload (GPP); Shuttle Amateur Radio Experiment (SAREX) II Radio Experiment (SAREX) II Radio Experiment (SAREX) II

Y-58 Y-58 Y-58 STS-72 Mission Facts — Endeavour — STS-72 Mission Facts — Endeavour — STS-72 Mission Facts — Endeavour — January 11–20, 1996 January 11–20, 1996 January 11–20, 1996

Commander: Brian K. Duffy Commander: Brian K. Duffy Commander: Brian K. Duffy Pilot: Brent W. Jett, Jr. Pilot: Brent W. Jett, Jr. Pilot: Brent W. Jett, Jr. Mission Specialist 1: Leroy Chiao Mission Specialist 1: Leroy Chiao Mission Specialist 1: Leroy Chiao Mission Specialist 2: Winston E. Scott Mission Specialist 2: Winston E. Scott Mission Specialist 2: Winston E. Scott Mission Specialist 3: Koichi Wakata, National Space Mission Specialist 3: Koichi Wakata, National Space Mission Specialist 3: Koichi Wakata, National Space Development Agency of Japan Development Agency of Japan Development Agency of Japan Mission Specialist 4: Daniel T. Barry Mission Specialist 4: Daniel T. Barry Mission Specialist 4: Daniel T. Barry Mission Duration: 192 hours (8 days), 22 hours, Mission Duration: 192 hours (8 days), 22 hours, Mission Duration: 192 hours (8 days), 22 hours, 1 minute, 47 seconds 1 minute, 47 seconds 1 minute, 47 seconds Miles Traveled: Approximately 3.7 million Miles Traveled: Approximately 3.7 million Miles Traveled: Approximately 3.7 million statute miles statute miles statute miles Inclination: 28.45 degrees Inclination: 28.45 degrees Inclination: 28.45 degrees Orbits of Earth: 142 Orbits of Earth: 142 Orbits of Earth: 142 Orbital Altitude: 250 nautical miles (288 statute miles) Orbital Altitude: 250 nautical miles (288 statute miles) Orbital Altitude: 250 nautical miles (288 statute miles) Landing Touchdown: Approximately 3,386 feet beyond Landing Touchdown: Approximately 3,386 feet beyond Landing Touchdown: Approximately 3,386 feet beyond threshold threshold threshold Landing Rollout: Approximately 8,070 feet Landing Rollout: Approximately 8,070 feet Landing Rollout: Approximately 8,070 feet Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately 217,269 pounds 217,269 pounds 217,269 pounds Lift-off Weight: Approximately 4,514,955 pounds Lift-off Weight: Approximately 4,514,955 pounds Lift-off Weight: Approximately 4,514,955 pounds Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately 247,319 pounds 247,319 pounds 247,319 pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 185 knots (213 miles per hour) mately 185 knots (213 miles per hour) mately 185 knots (213 miles per hour) Payload Weight Up: Approximately 14,353 pounds Payload Weight Up: Approximately 14,353 pounds Payload Weight Up: Approximately 14,353 pounds Payload Weight Down: Approximately 22,233 pounds Payload Weight Down: Approximately 22,233 pounds Payload Weight Down: Approximately 22,233 pounds Landed: Concrete runway 15 at Kennedy Space Center, Landed: Concrete runway 15 at Kennedy Space Center, Landed: Concrete runway 15 at Kennedy Space Center, Florida Florida Florida Payloads: Space Flyer Unit (SFU) retrieval; Office of Payloads: Space Flyer Unit (SFU) retrieval; Office of Payloads: Space Flyer Unit (SFU) retrieval; Office of Aeronautics and Space Technology (OAST) Flyer; Aeronautics and Space Technology (OAST) Flyer; Aeronautics and Space Technology (OAST) Flyer; Shuttle Solar Backscatter Ultraviolet (SSBUV/A; Shuttle Solar Backscatter Ultraviolet (SSBUV/A; Shuttle Solar Backscatter Ultraviolet (SSBUV/A; Shuttle Laser Altimeter (SLA) 01/ Shuttle Laser Altimeter (SLA) 01/ Shuttle Laser Altimeter (SLA) 01/ Getaway Special (GAS)(5); Extravehicular Activity Getaway Special (GAS)(5); Extravehicular Activity Getaway Special (GAS)(5); Extravehicular Activity Development Flight Test (EDFT) 03; Physiologi- Development Flight Test (EDFT) 03; Physiologi- Development Flight Test (EDFT) 03; Physiologi- cal and Anatomical Rodent Experiment (PARE)/ cal and Anatomical Rodent Experiment (PARE)/ cal and Anatomical Rodent Experiment (PARE)/ National Institutes of Health (NIH) Rodents (R) National Institutes of Health (NIH) Rodents (R) National Institutes of Health (NIH) Rodents (R) 03; Protein Crystal Growth (PCG) Single-Locker 03; Protein Crystal Growth (PCG) Single-Locker 03; Protein Crystal Growth (PCG) Single-Locker Thermal Enclosure System Thermal Enclosure System Thermal Enclosure System (STES) 04; Commercial Protein Crystal Growth (STES) 04; Commercial Protein Crystal Growth (STES) 04; Commercial Protein Crystal Growth (CPCG) 08; Space Tissue Loss (STL)/National (CPCG) 08; Space Tissue Loss (STL)/National (CPCG) 08; Space Tissue Loss (STL)/National Institutes of Health (NIH) Cells (C) 05 Institutes of Health (NIH) Cells (C) 05 Institutes of Health (NIH) Cells (C) 05 Extravehicular Activity (EVA): EVA No. 1, Leroy Chiao Extravehicular Activity (EVA): EVA No. 1, Leroy Chiao Extravehicular Activity (EVA): EVA No. 1, Leroy Chiao and Daniel T. Barry, 6 hours, 9 minutes; EVA No. and Daniel T. Barry, 6 hours, 9 minutes; EVA No. and Daniel T. Barry, 6 hours, 9 minutes; EVA No. 2, Leroy Chiao and Winston E. Scott, 6 hours, 53 2, Leroy Chiao and Winston E. Scott, 6 hours, 53 2, Leroy Chiao and Winston E. Scott, 6 hours, 53 minutes. Chiao and Barry evaluated a new EVA minutes. Chiao and Barry evaluated a new EVA minutes. Chiao and Barry evaluated a new EVA workstation, a movable stanchion that provides workstation, a movable stanchion that provides workstation, a movable stanchion that provides stability for astronauts and holders for tools, a stability for astronauts and holders for tools, a stability for astronauts and holders for tools, a flexible foot restraint, and a rigid umbilical that may flexible foot restraint, and a rigid umbilical that may flexible foot restraint, and a rigid umbilical that may be used on the International Space Station to hold be used on the International Space Station to hold be used on the International Space Station to hold fluid and electrical umbilicals in place. fluid and electrical umbilicals in place. fluid and electrical umbilicals in place.

Y-59 Y-59 Y-59 STS-72 Mission Facts (Cont) STS-72 Mission Facts (Cont) STS-72 Mission Facts (Cont)

Chiao and Scott evaluated a utility box designed Chiao and Scott evaluated a utility box designed Chiao and Scott evaluated a utility box designed to hold avionics and fluid line connections on the to hold avionics and fluid line connections on the to hold avionics and fluid line connections on the space station, an on-orbit-installed slidewire to space station, an on-orbit-installed slidewire to space station, an on-orbit-installed slidewire to which tethers can be connected, thermal improve- which tethers can be connected, thermal improve- which tethers can be connected, thermal improve- ments of space suits, and a wrist-mounted com- ments of space suits, and a wrist-mounted com- ments of space suits, and a wrist-mounted com- puter called the electronic cuff checklist. They also puter called the electronic cuff checklist. They also puter called the electronic cuff checklist. They also took measurements of the forces induced by work. took measurements of the forces induced by work. took measurements of the forces induced by work.

STS-75 Mission Facts — Columbia — STS-75 Mission Facts — Columbia — STS-75 Mission Facts — Columbia — February 22–March 9, 1996 February 22–March 9, 1996 February 22–March 9, 1996

Commander: Andrew M. Allen Commander: Andrew M. Allen Commander: Andrew M. Allen Pilot: Scott J. “Doc” Horowitz Pilot: Scott J. “Doc” Horowitz Pilot: Scott J. “Doc” Horowitz Payload Commander: Franklin R. Chang-Diaz Payload Commander: Franklin R. Chang-Diaz Payload Commander: Franklin R. Chang-Diaz Mission Specialist 1: Jeffrey A. Hoffman Mission Specialist 1: Jeffrey A. Hoffman Mission Specialist 1: Jeffrey A. Hoffman Mission Specialist 2: Maurizio Cheli, European Space Mission Specialist 2: Maurizio Cheli, European Space Mission Specialist 2: Maurizio Cheli, European Space Agency Agency Agency Mission Specialist 3: Claude Nicollier, European Space Mission Specialist 3: Claude Nicollier, European Space Mission Specialist 3: Claude Nicollier, European Space Agency Agency Agency Payload Specialist: Umberto Guidoni, Italian Space Payload Specialist: Umberto Guidoni, Italian Space Payload Specialist: Umberto Guidoni, Italian Space Agency Agency Agency Mission Duration: 360 hours (15 days), 17 hours, Mission Duration: 360 hours (15 days), 17 hours, Mission Duration: 360 hours (15 days), 17 hours, 40 minutes, 21 seconds 40 minutes, 21 seconds 40 minutes, 21 seconds Miles Traveled: Approximately 6.5 million statute miles Miles Traveled: Approximately 6.5 million statute miles Miles Traveled: Approximately 6.5 million statute miles Inclination: 28.45 degrees Inclination: 28.45 degrees Inclination: 28.45 degrees Orbits of Earth: 252 Orbits of Earth: 252 Orbits of Earth: 252 Orbital Altitude: 160 nautical miles (184 statute miles) Orbital Altitude: 160 nautical miles (184 statute miles) Orbital Altitude: 160 nautical miles (184 statute miles) Landing Touchdown: Approximately 2,175 feet beyond Landing Touchdown: Approximately 2,175 feet beyond Landing Touchdown: Approximately 2,175 feet beyond threshold threshold threshold Landing Rollout: Approximately 8,460 feet Landing Rollout: Approximately 8,460 feet Landing Rollout: Approximately 8,460 feet Orbiter Weight at Landing: 228,571 pounds Orbiter Weight at Landing: 228,571 pounds Orbiter Weight at Landing: 228,571 pounds Lift-off Weight: Approximately 4,526,493 pounds Lift-off Weight: Approximately 4,526,493 pounds Lift-off Weight: Approximately 4,526,493 pounds Orbiter Weight at Lift-off: Approximately 261,491 Orbiter Weight at Lift-off: Approximately 261,491 Orbiter Weight at Lift-off: Approximately 261,491 pounds pounds pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 189 knots (217 miles per hour) mately 189 knots (217 miles per hour) mately 189 knots (217 miles per hour) Payload Weight Up: Approximately 23,353 pounds Payload Weight Up: Approximately 23,353 pounds Payload Weight Up: Approximately 23,353 pounds Payload Weight Down: 23,263 pounds Payload Weight Down: 23,263 pounds Payload Weight Down: 23,263 pounds Landed: Concrete runway 33 at Kennedy Space Center, Landed: Concrete runway 33 at Kennedy Space Center, Landed: Concrete runway 33 at Kennedy Space Center, Florida Florida Florida Payloads: Tethered Satellite System (TSS) Reflight (1R); Payloads: Tethered Satellite System (TSS) Reflight (1R); Payloads: Tethered Satellite System (TSS) Reflight (1R); Orbital Acceleration Research Experiment (OARE) Orbital Acceleration Research Experiment (OARE) Orbital Acceleration Research Experiment (OARE) (part of United States Microgravity Payload 3); (part of United States Microgravity Payload 3); (part of United States Microgravity Payload 3); USMP-3; Commercial Protein Crystal Growth USMP-3; Commercial Protein Crystal Growth USMP-3; Commercial Protein Crystal Growth (CPCG) 09, Block IV; Middeck Glovebox Experi- (CPCG) 09, Block IV; Middeck Glovebox Experi- (CPCG) 09, Block IV; Middeck Glovebox Experi- ment (MGBX) (part of USMP-3) ment (MGBX) (part of USMP-3) ment (MGBX) (part of USMP-3)

During the deployment of TSS, the tether broke During the deployment of TSS, the tether broke During the deployment of TSS, the tether broke and the satellite was lost. and the satellite was lost. and the satellite was lost.

Y-60 Y-60 Y-60 STS-76 Mission Facts — Atlantis — STS-76 Mission Facts — Atlantis — STS-76 Mission Facts — Atlantis — March 22–31, 1996 March 22–31, 1996 March 22–31, 1996

Commander: Kevin P. Chilton Commander: Kevin P. Chilton Commander: Kevin P. Chilton Pilot: Richard A. Searfoss Pilot: Richard A. Searfoss Pilot: Richard A. Searfoss Mission Specialist: Shannon W. Lucid—up only Mission Specialist: Shannon W. Lucid—up only Mission Specialist: Shannon W. Lucid—up only Mission Specialist: Linda M. Godwin Mission Specialist: Linda M. Godwin Mission Specialist: Linda M. Godwin Mission Specialist: Michael R. “Rich” Clifford Mission Specialist: Michael R. “Rich” Clifford Mission Specialist: Michael R. “Rich” Clifford Mission Specialist: Ronald M. Sega Mission Specialist: Ronald M. Sega Mission Specialist: Ronald M. Sega Mission Duration: 216 hours (9 days), 5 hours, Mission Duration: 216 hours (9 days), 5 hours, Mission Duration: 216 hours (9 days), 5 hours, 16 minutes, 48 seconds 16 minutes, 48 seconds 16 minutes, 48 seconds Miles Traveled: Approximately 3.8 million statute miles Miles Traveled: Approximately 3.8 million statute miles Miles Traveled: Approximately 3.8 million statute miles Inclination: 51.6 degrees Inclination: 51.6 degrees Inclination: 51.6 degrees Orbits of Earth: 145 Orbits of Earth: 145 Orbits of Earth: 145 Orbital Altitude: 160 nautical miles (184 statute miles) Orbital Altitude: 160 nautical miles (184 statute miles) Orbital Altitude: 160 nautical miles (184 statute miles) insertion; 213 nautical miles (245 statute miles) for insertion; 213 nautical miles (245 statute miles) for insertion; 213 nautical miles (245 statute miles) for Mir rendezvous Mir rendezvous Mir rendezvous Landing Touchdown: Approximately 2,222 feet beyond Landing Touchdown: Approximately 2,222 feet beyond Landing Touchdown: Approximately 2,222 feet beyond threshold threshold threshold Landing Rollout: Approximately 8,357 feet Landing Rollout: Approximately 8,357 feet Landing Rollout: Approximately 8,357 feet Orbiter Weight at Landing: Approximately 210,316 Orbiter Weight at Landing: Approximately 210,316 Orbiter Weight at Landing: Approximately 210,316 pounds pounds pounds Lift-off Weight: Approximately 4,509,503 pounds Lift-off Weight: Approximately 4,509,503 pounds Lift-off Weight: Approximately 4,509,503 pounds Orbiter Weight at Lift-off: Approximately 246,345 Orbiter Weight at Lift-off: Approximately 246,345 Orbiter Weight at Lift-off: Approximately 246,345 pounds pounds pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 204 knots (235 miles per hour) mately 204 knots (235 miles per hour) mately 204 knots (235 miles per hour) Payload Weight Up: Approximately 14,888 pounds Payload Weight Up: Approximately 14,888 pounds Payload Weight Up: Approximately 14,888 pounds Payload Weight Down: Approximately 12,058 pounds Payload Weight Down: Approximately 12,058 pounds Payload Weight Down: Approximately 12,058 pounds Landed: Concrete runway 22 at Edwards Air Force Landed: Concrete runway 22 at Edwards Air Force Landed: Concrete runway 22 at Edwards Air Force Base, California Base, California Base, California Payloads: Shuttle-Mir Mission 3; SPACEHAB/ Payloads: Shuttle-Mir Mission 3; SPACEHAB/ Payloads: Shuttle-Mir Mission 3; SPACEHAB/ Mir 03; KidSat; Shuttle Amateur Radio Experiment Mir 03; KidSat; Shuttle Amateur Radio Experiment Mir 03; KidSat; Shuttle Amateur Radio Experiment (SAREX) II, Configuration M; RME 1304—Mir/Envi- (SAREX) II, Configuration M; RME 1304—Mir/Envi- (SAREX) II, Configuration M; RME 1304—Mir/Envi- ronmental Effects Payload (MEEP); orbiter docking ronmental Effects Payload (MEEP); orbiter docking ronmental Effects Payload (MEEP); orbiter docking system; RME 1315—Trapped Ions in Space Ex- system; RME 1315—Trapped Ions in Space Ex- system; RME 1315—Trapped Ions in Space Ex- periment (TRIS); Extravehicular Activity Develop- periment (TRIS); Extravehicular Activity Develop- periment (TRIS); Extravehicular Activity Develop- ment Flight Test (EDFT) 04 ment Flight Test (EDFT) 04 ment Flight Test (EDFT) 04 Extravehicular Activity (EVA): Linda M. Godwin and Extravehicular Activity (EVA): Linda M. Godwin and Extravehicular Activity (EVA): Linda M. Godwin and Michael R. “Rich” Clifford, 6 hours, 2 minutes, Michael R. “Rich” Clifford, 6 hours, 2 minutes, Michael R. “Rich” Clifford, 6 hours, 2 minutes, 28 seconds. Godwin and Clifford attached four 28 seconds. Godwin and Clifford attached four 28 seconds. Godwin and Clifford attached four experiments, known collectively as MEEP, onto experiments, known collectively as MEEP, onto experiments, known collectively as MEEP, onto handrails located on Mir’s docking module. They handrails located on Mir’s docking module. They handrails located on Mir’s docking module. They also detached a television camera from the out- also detached a television camera from the out- also detached a television camera from the out- side of the Mir docking module to return it to Earth, side of the Mir docking module to return it to Earth, side of the Mir docking module to return it to Earth, and evaluated a variety of new spacewalking tools and evaluated a variety of new spacewalking tools and evaluated a variety of new spacewalking tools capable of being used on both the U.S. and Rus- capable of being used on both the U.S. and Rus- capable of being used on both the U.S. and Rus- sian spacecraft. sian spacecraft. sian spacecraft.

Y-61 Y-61 Y-61 STS-77 Mission Facts — Endeavour — STS-77 Mission Facts — Endeavour — STS-77 Mission Facts — Endeavour — May 19–29, 1996 May 19–29, 1996 May 19–29, 1996 Commander: John H. Casper Commander: John H. Casper Commander: John H. Casper Pilot: Curtis L. Brown, Jr. Pilot: Curtis L. Brown, Jr. Pilot: Curtis L. Brown, Jr. Mission Specialist: Daniel W. Bursch Mission Specialist: Daniel W. Bursch Mission Specialist: Daniel W. Bursch Mission Specialist: Andrew S.W. Thomas Mission Specialist: Andrew S.W. Thomas Mission Specialist: Andrew S.W. Thomas Mission Specialist: Marc Garneau, Canadian Space Mission Specialist: Marc Garneau, Canadian Space Mission Specialist: Marc Garneau, Canadian Space Agency Agency Agency Mission Specialist: Mario Runco, Jr. Mission Specialist: Mario Runco, Jr. Mission Specialist: Mario Runco, Jr. Mission Duration: 240 hours (10 days), 0 hours, Mission Duration: 240 hours (10 days), 0 hours, Mission Duration: 240 hours (10 days), 0 hours, 40 minutes, 10 seconds 40 minutes, 10 seconds 40 minutes, 10 seconds Miles Traveled: Approximately 4.1 million statute miles Miles Traveled: Approximately 4.1 million statute miles Miles Traveled: Approximately 4.1 million statute miles Inclination: 39 degrees Inclination: 39 degrees Inclination: 39 degrees Orbits of Earth: 161 Orbits of Earth: 161 Orbits of Earth: 161 Orbital Altitude: 153 nautical miles (176 statute miles) Orbital Altitude: 153 nautical miles (176 statute miles) Orbital Altitude: 153 nautical miles (176 statute miles) Landing Touchdown: Approximately 1,688 feet beyond Landing Touchdown: Approximately 1,688 feet beyond Landing Touchdown: Approximately 1,688 feet beyond threshold threshold threshold Landing Rollout: Approximately 9,290 feet Landing Rollout: Approximately 9,290 feet Landing Rollout: Approximately 9,290 feet Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately 221,382 pounds 221,382 pounds 221,382 pounds Lift-off Weight: Approximately 4,518,947 pounds Lift-off Weight: Approximately 4,518,947 pounds Lift-off Weight: Approximately 4,518,947 pounds Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately 254,538 pounds 254,538 pounds 254,538 pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 215 knots (247 miles per hour) mately 215 knots (247 miles per hour) mately 215 knots (247 miles per hour) Payload Weight Up: Approximately 26,971 pounds Payload Weight Up: Approximately 26,971 pounds Payload Weight Up: Approximately 26,971 pounds Payload Weight Down: Approximately 26,149 pounds Payload Weight Down: Approximately 26,149 pounds Payload Weight Down: Approximately 26,149 pounds Landed: Concrete runway 33 at Kennedy Space Center, Landed: Concrete runway 33 at Kennedy Space Center, Landed: Concrete runway 33 at Kennedy Space Center, Florida Florida Florida Payloads: Shuttle Pointed Research Tool for Astronomy Payloads: Shuttle Pointed Research Tool for Astronomy Payloads: Shuttle Pointed Research Tool for Astronomy (SPARTAN) 207/Inflatable Antenna Experiment (SPARTAN) 207/Inflatable Antenna Experiment (SPARTAN) 207/Inflatable Antenna Experiment (IAE); Technology Experiments Advancing Mis- (IAE); Technology Experiments Advancing Mis- (IAE); Technology Experiments Advancing Mis- sions in Space (TEAMS) 01 (includes Vented Tank sions in Space (TEAMS) 01 (includes Vented Tank sions in Space (TEAMS) 01 (includes Vented Tank Resupply Experiment [VTRE], Global Positioning Resupply Experiment [VTRE], Global Positioning Resupply Experiment [VTRE], Global Positioning System [GPS] Attitude and Navigation Experiment System [GPS] Attitude and Navigation Experiment System [GPS] Attitude and Navigation Experiment [GANE] [RME 1316], Liquid Metal Test Experiment [GANE] [RME 1316], Liquid Metal Test Experiment [GANE] [RME 1316], Liquid Metal Test Experiment [LMTE] and Passive Aerodynamically Stabilized [LMTE] and Passive Aerodynamically Stabilized [LMTE] and Passive Aerodynamically Stabilized Magnetically Damped Satellite [PAMS] Satellite Magnetically Damped Satellite [PAMS] Satellite Magnetically Damped Satellite [PAMS] Satellite Test Unit [STU]; SPACEHAB-4; Brilliant Eyes Ten- Test Unit [STU]; SPACEHAB-4; Brilliant Eyes Ten- Test Unit [STU]; SPACEHAB-4; Brilliant Eyes Ten- Kelvin Sorption Cryocooler Experiment (BETSCE); Kelvin Sorption Cryocooler Experiment (BETSCE); Kelvin Sorption Cryocooler Experiment (BETSCE); 12 getaway specials attached to a GAS bridge 12 getaway specials attached to a GAS bridge 12 getaway specials attached to a GAS bridge assembly (GAS 056, 063, 142, 144, 163, 200, 490, assembly (GAS 056, 063, 142, 144, 163, 200, 490, assembly (GAS 056, 063, 142, 144, 163, 200, 490, 564, 565, 703, 741 and the Reduced-Fill Tank 564, 565, 703, 741 and the Reduced-Fill Tank 564, 565, 703, 741 and the Reduced-Fill Tank Pressure Control Experiment [RFTPCE]; Aquatic Pressure Control Experiment [RFTPCE]; Aquatic Pressure Control Experiment [RFTPCE]; Aquatic Research Facility (ARF) 01; Biological Research in Research Facility (ARF) 01; Biological Research in Research Facility (ARF) 01; Biological Research in Canisters (BRIC) 07, Block III Canisters (BRIC) 07, Block III Canisters (BRIC) 07, Block III STS-78 Mission Facts – Columbia STS-78 Mission Facts – Columbia STS-78 Mission Facts – Columbia June 20–July 7, 1996 June 20–July 7, 1996 June 20–July 7, 1996

Commander: Terence T. "Tom" Henricks Commander: Terence T. "Tom" Henricks Commander: Terence T. "Tom" Henricks Pilot: Kevin R. Kregel Pilot: Kevin R. Kregel Pilot: Kevin R. Kregel Mission Specialist: Susan J. Helms Mission Specialist: Susan J. Helms Mission Specialist: Susan J. Helms Mission Specialist: Richard M. Linnehan Mission Specialist: Richard M. Linnehan Mission Specialist: Richard M. Linnehan

Y-62 Y-62 Y-62 STS-78 Mission Facts (Cont) STS-78 Mission Facts (Cont) STS-78 Mission Facts (Cont)

Mission Specialist: Charles E. Brady, Jr. Mission Specialist: Charles E. Brady, Jr. Mission Specialist: Charles E. Brady, Jr. Payload Specialist: Jean-Jacques Favier, French Payload Specialist: Jean-Jacques Favier, French Payload Specialist: Jean-Jacques Favier, French Atomic Energy Commission (CEA), French Space Atomic Energy Commission (CEA), French Space Atomic Energy Commission (CEA), French Space Agency (CNES) Agency (CNES) Agency (CNES) Payload Specialist: Robert Brent Thirsk, Canadian Payload Specialist: Robert Brent Thirsk, Canadian Payload Specialist: Robert Brent Thirsk, Canadian Space Agency Space Agency Space Agency Mission Duration: 384 hours (16 days), 21 hours, Mission Duration: 384 hours (16 days), 21 hours, Mission Duration: 384 hours (16 days), 21 hours, 48 minutes, 30 seconds 48 minutes, 30 seconds 48 minutes, 30 seconds Miles Traveled: Approximately 7 million statute miles Miles Traveled: Approximately 7 million statute miles Miles Traveled: Approximately 7 million statute miles Inclination: 39 degrees Inclination: 39 degrees Inclination: 39 degrees Orbits of Earth: 272 Orbits of Earth: 272 Orbits of Earth: 272 Orbital Altitude: 150 nautical miles (173 statute miles) Orbital Altitude: 150 nautical miles (173 statute miles) Orbital Altitude: 150 nautical miles (173 statute miles) Landing Touchdown: Approximately 2,304 feet beyond Landing Touchdown: Approximately 2,304 feet beyond Landing Touchdown: Approximately 2,304 feet beyond threshold threshold threshold Landing Rollout: Approximately 9,290 feet Landing Rollout: Approximately 9,290 feet Landing Rollout: Approximately 9,290 feet Orbiter Weight at Landing: Approximately 228,009 Orbiter Weight at Landing: Approximately 228,009 Orbiter Weight at Landing: Approximately 228,009 pounds pounds pounds Lift-off Weight: Approximately 4,517,981 pounds Lift-off Weight: Approximately 4,517,981 pounds Lift-off Weight: Approximately 4,517,981 pounds Orbiter Weight at Lift-off: Approximately 254,823 Orbiter Weight at Lift-off: Approximately 254,823 Orbiter Weight at Lift-off: Approximately 254,823 pounds pounds pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 208 knots (239 mph) mately 208 knots (239 mph) mately 208 knots (239 mph) Payload Weight Up: Approximately 23,537 pounds Payload Weight Up: Approximately 23,537 pounds Payload Weight Up: Approximately 23,537 pounds Payload Weight Down: Approximately 23,537 pounds Payload Weight Down: Approximately 23,537 pounds Payload Weight Down: Approximately 23,537 pounds Landed: Concrete runway 33 at Kennedy Space Center, Landed: Concrete runway 33 at Kennedy Space Center, Landed: Concrete runway 33 at Kennedy Space Center, Florida Florida Florida Payloads: Life and Microgravity Sciences (LMS) 01 Payloads: Life and Microgravity Sciences (LMS) 01 Payloads: Life and Microgravity Sciences (LMS) 01 Spacelab with long crew transfer tunnel; Orbital Spacelab with long crew transfer tunnel; Orbital Spacelab with long crew transfer tunnel; Orbital Acceleration Research Experiment (OARE); Acceleration Research Experiment (OARE); Acceleration Research Experiment (OARE); extended-duration orbiter cryogenic pallet; extended-duration orbiter cryogenic pallet; extended-duration orbiter cryogenic pallet; Biological Research in Canisters (BRIC) 8, Block II; Biological Research in Canisters (BRIC) 8, Block II; Biological Research in Canisters (BRIC) 8, Block II; Shuttle Amateur Radio Experiment (SAREX) II, Shuttle Amateur Radio Experiment (SAREX) II, Shuttle Amateur Radio Experiment (SAREX) II, Configuration C Configuration C Configuration C

STS-79 Mission Facts – Atlantis – STS-79 Mission Facts – Atlantis – STS-79 Mission Facts – Atlantis – September 16–26, 1996 September 16–26, 1996 September 16–26, 1996

Commander: William F. Readdy Commander: William F. Readdy Commander: William F. Readdy Pilot: Terrence W. Wilcutt Pilot: Terrence W. Wilcutt Pilot: Terrence W. Wilcutt Mission Specialist: Thomas D. Akers Mission Specialist: Thomas D. Akers Mission Specialist: Thomas D. Akers Mission Specialist: Jerome Apt Mission Specialist: Jerome Apt Mission Specialist: Jerome Apt Mission Specialist: Carl E. Walz Mission Specialist: Carl E. Walz Mission Specialist: Carl E. Walz Mission Specialist: John E. Blaha—up only Mission Specialist: John E. Blaha—up only Mission Specialist: John E. Blaha—up only Mir Crew Member: Shannon W. Lucid—down only Mir Crew Member: Shannon W. Lucid—down only Mir Crew Member: Shannon W. Lucid—down only Mission Duration: 240 hours (10 days), 3 hours, 18 min- Mission Duration: 240 hours (10 days), 3 hours, 18 min- Mission Duration: 240 hours (10 days), 3 hours, 18 min- utes, 24 seconds utes, 24 seconds utes, 24 seconds Miles Traveled: Approximately 3.9 million statute miles Miles Traveled: Approximately 3.9 million statute miles Miles Traveled: Approximately 3.9 million statute miles Inclination: 51.6 degrees Inclination: 51.6 degrees Inclination: 51.6 degrees Orbits of Earth: 160 Orbits of Earth: 160 Orbits of Earth: 160 Orbital Altitude: 170 nautical miles (196 statute miles) Orbital Altitude: 170 nautical miles (196 statute miles) Orbital Altitude: 170 nautical miles (196 statute miles) insertion; 213 nautical miles (245 statute miles) for insertion; 213 nautical miles (245 statute miles) for insertion; 213 nautical miles (245 statute miles) for Mir rendezvous Mir rendezvous Mir rendezvous Y-63 Y-63 Y-63 STS-79 Mission Facts (Cont) STS-79 Mission Facts (Cont) STS-79 Mission Facts (Cont)

Landing Touchdown: Approximately 807 feet beyond Landing Touchdown: Approximately 807 feet beyond Landing Touchdown: Approximately 807 feet beyond threshold threshold threshold Landing Rollout: Approximately 10,981 feet Landing Rollout: Approximately 10,981 feet Landing Rollout: Approximately 10,981 feet Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately 215,176 pounds 215,176 pounds 215,176 pounds Lift-off Weight: Approximately 4,510,356 pounds Lift-off Weight: Approximately 4,510,356 pounds Lift-off Weight: Approximately 4,510,356 pounds Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately 249,327 pounds 249,327 pounds 249,327 pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 217 knots (250 miles per hour) mately 217 knots (250 miles per hour) mately 217 knots (250 miles per hour) Payload Weight Up: Approximately 19,516 pounds Payload Weight Up: Approximately 19,516 pounds Payload Weight Up: Approximately 19,516 pounds Payload Weight Down: Approximately 18,346 pounds Payload Weight Down: Approximately 18,346 pounds Payload Weight Down: Approximately 18,346 pounds Landed: Concrete runway 15 at Kennedy Space Center, Landed: Concrete runway 15 at Kennedy Space Center, Landed: Concrete runway 15 at Kennedy Space Center, Florida Florida Florida Payloads: Shuttle/Mir Mission 04; SPACEHAB/Mir 05; Payloads: Shuttle/Mir Mission 04; SPACEHAB/Mir 05; Payloads: Shuttle/Mir Mission 04; SPACEHAB/Mir 05; orbiter docking system; Shuttle/Mir Mission 04 orbiter docking system; Shuttle/Mir Mission 04 orbiter docking system; Shuttle/Mir Mission 04 middeck science; Shuttle Amateur Radio Experi- middeck science; Shuttle Amateur Radio Experi- middeck science; Shuttle Amateur Radio Experi- ment (SAREX) II, configuration M; IMAX ment (SAREX) II, configuration M; IMAX ment (SAREX) II, configuration M; IMAX in-cabin camera; Midcourse Space Experiment in-cabin camera; Midcourse Space Experiment in-cabin camera; Midcourse Space Experiment (MSX) (MSX) (MSX)

STS-80 Mission Facts – Columbia – STS-80 Mission Facts – Columbia – STS-80 Mission Facts – Columbia – November 19–December 7, 1996 November 19–December 7, 1996 November 19–December 7, 1996

Commander: Kenneth D. Cockrell Commander: Kenneth D. Cockrell Commander: Kenneth D. Cockrell Pilot: Kent V. Rominger Pilot: Kent V. Rominger Pilot: Kent V. Rominger Mission Specialist: Tamara E. Jernigan Mission Specialist: Tamara E. Jernigan Mission Specialist: Tamara E. Jernigan Mission Specialist: Thomas David Jones Mission Specialist: Thomas David Jones Mission Specialist: Thomas David Jones Mission Specialist: F. Story Musgrave Mission Specialist: F. Story Musgrave Mission Specialist: F. Story Musgrave Mission Duration: 408 hours (17 days), 15 hours, Mission Duration: 408 hours (17 days), 15 hours, Mission Duration: 408 hours (17 days), 15 hours, 54 minutes, 28 seconds 54 minutes, 28 seconds 54 minutes, 28 seconds Miles Traveled: Approximately 7.6 million statute miles Miles Traveled: Approximately 7.6 million statute miles Miles Traveled: Approximately 7.6 million statute miles Inclination: 28.45 degrees Inclination: 28.45 degrees Inclination: 28.45 degrees Orbits of Earth: 279 Orbits of Earth: 279 Orbits of Earth: 279 Orbital Altitude: 190 nautical miles (219 statute miles) Orbital Altitude: 190 nautical miles (219 statute miles) Orbital Altitude: 190 nautical miles (219 statute miles) Landing Touchdown: Approximately 3,084 feet beyond Landing Touchdown: Approximately 3,084 feet beyond Landing Touchdown: Approximately 3,084 feet beyond threshold threshold threshold Landing Rollout: Approximately 8,705 feet Landing Rollout: Approximately 8,705 feet Landing Rollout: Approximately 8,705 feet Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately 227,879 pounds 227,879 pounds 227,879 pounds Lift-off Weight: Approximately 4,525,340 pounds Lift-off Weight: Approximately 4,525,340 pounds Lift-off Weight: Approximately 4,525,340 pounds Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately 261,910 pounds 261,910 pounds 261,910 pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 371 knots (427 miles per hour) mately 371 knots (427 miles per hour) mately 371 knots (427 miles per hour) Payload Weight Up: Approximately 21,489 pounds Payload Weight Up: Approximately 21,489 pounds Payload Weight Up: Approximately 21,489 pounds Payload Weight Down: Approximately 21,387 pounds Payload Weight Down: Approximately 21,387 pounds Payload Weight Down: Approximately 21,387 pounds Landed: Concrete runway 33 at Kennedy Space Center, Landed: Concrete runway 33 at Kennedy Space Center, Landed: Concrete runway 33 at Kennedy Space Center, Florida Florida Florida

Y-64 Y-64 Y-64 STS-80 Mission Facts (Cont) STS-80 Mission Facts (Cont) STS-80 Mission Facts (Cont) Payloads: Wake Shield Facility (WSF) 03; Orbiting and Payloads: Wake Shield Facility (WSF) 03; Orbiting and Payloads: Wake Shield Facility (WSF) 03; Orbiting and Retrievable Far and Extreme Ultraviolet Spectro- Retrievable Far and Extreme Ultraviolet Spectro- Retrievable Far and Extreme Ultraviolet Spectro- graph—Shuttle Pallet Satellite (ORFEUS-SPAS) II; graph—Shuttle Pallet Satellite (ORFEUS-SPAS) II; graph—Shuttle Pallet Satellite (ORFEUS-SPAS) II; Inter-Mars Tissue Equivalent Proportional Counter Inter-Mars Tissue Equivalent Proportional Counter Inter-Mars Tissue Equivalent Proportional Counter (ITEPC) (also known as DSO 485); Extravehicular (ITEPC) (also known as DSO 485); Extravehicular (ITEPC) (also known as DSO 485); Extravehicular Activity Development Flight Test (EDFT) 05; Space Activity Development Flight Test (EDFT) 05; Space Activity Development Flight Test (EDFT) 05; Space Experiment Module (SEM) 01/Getaway Special Experiment Module (SEM) 01/Getaway Special Experiment Module (SEM) 01/Getaway Special (GAS); Physiological and Anatomical Rodent (GAS); Physiological and Anatomical Rodent (GAS); Physiological and Anatomical Rodent Experiment (PARE)/National Institutes of Health Experiment (PARE)/National Institutes of Health Experiment (PARE)/National Institutes of Health (NIH)-Rodents (R) 04; Commercial Materials (NIH)-Rodents (R) 04; Commercial Materials (NIH)-Rodents (R) 04; Commercial Materials Dispersions Apparatus (MDA) Instrumentation Dispersions Apparatus (MDA) Instrumentation Dispersions Apparatus (MDA) Instrumentation Technology Associates (ITA) Experiments (CMIX) Technology Associates (ITA) Experiments (CMIX) Technology Associates (ITA) Experiments (CMIX) 05, Configuration B; Visualization in an Experimen- 05, Configuration B; Visualization in an Experimen- 05, Configuration B; Visualization in an Experimen- tal Water Capillary Pumped Loop (VIEW-CPL); Cell tal Water Capillary Pumped Loop (VIEW-CPL); Cell tal Water Capillary Pumped Loop (VIEW-CPL); Cell Culture Module (CCM), Configuration A; Biological Culture Module (CCM), Configuration A; Biological Culture Module (CCM), Configuration A; Biological Research in Canisters (BRIC) 09, Block 1; Mid- Research in Canisters (BRIC) 09, Block 1; Mid- Research in Canisters (BRIC) 09, Block 1; Mid- course Space Experiment (payload of opportunity) course Space Experiment (payload of opportunity) course Space Experiment (payload of opportunity) Due to problems in opening Columbia’s airlock Due to problems in opening Columbia’s airlock Due to problems in opening Columbia’s airlock hatch, EDFT 05 could not be performed and no hatch, EDFT 05 could not be performed and no hatch, EDFT 05 could not be performed and no extravehicular activity occurred. extravehicular activity occurred. extravehicular activity occurred. STS-81 Mission Facts – Atlantis – STS-81 Mission Facts – Atlantis – STS-81 Mission Facts – Atlantis – January 12–22, 1997 January 12–22, 1997 January 12–22, 1997

Commander: Michael A. Baker Commander: Michael A. Baker Commander: Michael A. Baker Pilot: Brent W. Jett, Jr. Pilot: Brent W. Jett, Jr. Pilot: Brent W. Jett, Jr. Mission Specialist: John M. Grunsfeld Mission Specialist: John M. Grunsfeld Mission Specialist: John M. Grunsfeld Mission Specialist: Marsha S. Ivins Mission Specialist: Marsha S. Ivins Mission Specialist: Marsha S. Ivins Mission Specialist: Peter J.K. "Jeff" Wisoff Mission Specialist: Peter J.K. "Jeff" Wisoff Mission Specialist: Peter J.K. "Jeff" Wisoff Mission Specialist: Jerry M. Linenger—up only Mission Specialist: Jerry M. Linenger—up only Mission Specialist: Jerry M. Linenger—up only Mir Crew Member: John E. Blaha—down only Mir Crew Member: John E. Blaha—down only Mir Crew Member: John E. Blaha—down only Mission Duration: 240 hours (10 days), 4 hours, Mission Duration: 240 hours (10 days), 4 hours, Mission Duration: 240 hours (10 days), 4 hours, 56 minutes, 31 seconds 56 minutes, 31 seconds 56 minutes, 31 seconds Miles Traveled: Approximately 3.8 million statute miles Miles Traveled: Approximately 3.8 million statute miles Miles Traveled: Approximately 3.8 million statute miles Inclination: 51.6 degrees Inclination: 51.6 degrees Inclination: 51.6 degrees Orbits of Earth: 161 Orbits of Earth: 161 Orbits of Earth: 161 Orbital Altitude: 160 nautical miles (184 statute miles) Orbital Altitude: 160 nautical miles (184 statute miles) Orbital Altitude: 160 nautical miles (184 statute miles) insertion; 213 nautical miles (245 statute miles) for insertion; 213 nautical miles (245 statute miles) for insertion; 213 nautical miles (245 statute miles) for Mir rendezvous Mir rendezvous Mir rendezvous Landing Touchdown: Approximately 2,926 feet beyond Landing Touchdown: Approximately 2,926 feet beyond Landing Touchdown: Approximately 2,926 feet beyond threshold threshold threshold Landing Rollout: Approximately 9,417 feet Landing Rollout: Approximately 9,417 feet Landing Rollout: Approximately 9,417 feet Orbiter Weight at Landing: Approximately 214,452 Orbiter Weight at Landing: Approximately 214,452 Orbiter Weight at Landing: Approximately 214,452 pounds pounds pounds Lift-off Weight: Approximately 4,510,780 pounds Lift-off Weight: Approximately 4,510,780 pounds Lift-off Weight: Approximately 4,510,780 pounds Orbiter Weight at Lift-off: Approximately 249,936 Orbiter Weight at Lift-off: Approximately 249,936 Orbiter Weight at Lift-off: Approximately 249,936 pounds pounds pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 369 knots (425 miles per hour) mately 369 knots (425 miles per hour) mately 369 knots (425 miles per hour) Payload Weight Up: Approximately 19,321 pounds Payload Weight Up: Approximately 19,321 pounds Payload Weight Up: Approximately 19,321 pounds

Y-65 Y-65 Y-65 STS-81 Mission Facts (Cont) STS-81 Mission Facts (Cont) STS-81 Mission Facts (Cont)

Payload Weight Down: Approximately 18,144 pounds Payload Weight Down: Approximately 18,144 pounds Payload Weight Down: Approximately 18,144 pounds Landed: Concrete runway 33 at Kennedy Space Center, Landed: Concrete runway 33 at Kennedy Space Center, Landed: Concrete runway 33 at Kennedy Space Center, Florida Florida Florida Payloads: SPACEHAB 06 double module, orbiter dock- Payloads: SPACEHAB 06 double module, orbiter dock- Payloads: SPACEHAB 06 double module, orbiter dock- ing system, Shuttle/Mir Mission 05 middeck science, ing system, Shuttle/Mir Mission 05 middeck science, ing system, Shuttle/Mir Mission 05 middeck science, Midcourse Space Experiment (MSX), Cosmic Radia- Midcourse Space Experiment (MSX), Cosmic Radia- Midcourse Space Experiment (MSX), Cosmic Radia- tion Effects and Activation Monitor (CREAM), KidSat tion Effects and Activation Monitor (CREAM), KidSat tion Effects and Activation Monitor (CREAM), KidSat STS-82 Mission Facts – Discovery – STS-82 Mission Facts – Discovery – STS-82 Mission Facts – Discovery – February 11–21, 1997 February 11–21, 1997 February 11–21, 1997

Commander: Kenneth D. Bowersox Commander: Kenneth D. Bowersox Commander: Kenneth D. Bowersox Pilot: Scott J. “Doc” Horowitz Pilot: Scott J. “Doc” Horowitz Pilot: Scott J. “Doc” Horowitz Mission Specialist: Mark C. Lee Mission Specialist: Mark C. Lee Mission Specialist: Mark C. Lee Mission Specialist: Gregory J. Harbaugh Mission Specialist: Gregory J. Harbaugh Mission Specialist: Gregory J. Harbaugh Mission Specialist: Steven L. Smith Mission Specialist: Steven L. Smith Mission Specialist: Steven L. Smith Mission Specialist: Joseph R. Tanner Mission Specialist: Joseph R. Tanner Mission Specialist: Joseph R. Tanner Mission Specialist: Steven A. Hawley Mission Specialist: Steven A. Hawley Mission Specialist: Steven A. Hawley Mission Duration: 216 hours (9 days), 23 hours, Mission Duration: 216 hours (9 days), 23 hours, Mission Duration: 216 hours (9 days), 23 hours, 38 minutes, 9 seconds 38 minutes, 9 seconds 38 minutes, 9 seconds Miles Traveled: Approximately 4.1 million statute miles Miles Traveled: Approximately 4.1 million statute miles Miles Traveled: Approximately 4.1 million statute miles Inclination: 28.45 degrees Inclination: 28.45 degrees Inclination: 28.45 degrees Orbits of Earth: 150 Orbits of Earth: 150 Orbits of Earth: 150 Orbital Altitude: 313 nautical miles (360 statute miles) Orbital Altitude: 313 nautical miles (360 statute miles) Orbital Altitude: 313 nautical miles (360 statute miles) orbital insertion; 320 nautical miles (369 statute orbital insertion; 320 nautical miles (369 statute orbital insertion; 320 nautical miles (369 statute miles) rendezvous miles) rendezvous miles) rendezvous Landing Touchdown: Approximately 2,607 feet beyond Landing Touchdown: Approximately 2,607 feet beyond Landing Touchdown: Approximately 2,607 feet beyond threshold threshold threshold Landing Rollout: Approximately 7,073 feet Landing Rollout: Approximately 7,073 feet Landing Rollout: Approximately 7,073 feet Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately 214,014 pounds 214,014 pounds 214,014 pounds Lift-off Weight: Approximately 4,514,520 pounds Lift-off Weight: Approximately 4,514,520 pounds Lift-off Weight: Approximately 4,514,520 pounds Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately 251,371 pounds 251,371 pounds 251,371 pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 184 knots (212 miles per hour) mately 184 knots (212 miles per hour) mately 184 knots (212 miles per hour) Payload Weight Up: Approximately 16,735 pounds Payload Weight Up: Approximately 16,735 pounds Payload Weight Up: Approximately 16,735 pounds Payload Weight Down: Approximately 16,429 pounds Payload Weight Down: Approximately 16,429 pounds Payload Weight Down: Approximately 16,429 pounds Landed: Concrete runway 15 at Kennedy Space Center, Landed: Concrete runway 15 at Kennedy Space Center, Landed: Concrete runway 15 at Kennedy Space Center, Florida Florida Florida Payloads: Hubble Space Telescope Servicing Mission Payloads: Hubble Space Telescope Servicing Mission Payloads: Hubble Space Telescope Servicing Mission 02 (second axial carrier, orbital replacement unit 02 (second axial carrier, orbital replacement unit 02 (second axial carrier, orbital replacement unit carrier, flight support system); Midcourse Space carrier, flight support system); Midcourse Space carrier, flight support system); Midcourse Space Experiment Experiment Experiment Extravehicular Activity (EVA): EVA 1, Mark C. Lee Extravehicular Activity (EVA): EVA 1, Mark C. Lee Extravehicular Activity (EVA): EVA 1, Mark C. Lee and Steven L. Smith, 6 hours, 42 minutes; EVA and Steven L. Smith, 6 hours, 42 minutes; EVA and Steven L. Smith, 6 hours, 42 minutes; EVA 2, Gregory J. Harbaugh and Joseph R. Tanner, 2, Gregory J. Harbaugh and Joseph R. Tanner, 2, Gregory J. Harbaugh and Joseph R. Tanner, 7 hours, 27 minutes; EVA 3, Mark C. Lee and 7 hours, 27 minutes; EVA 3, Mark C. Lee and 7 hours, 27 minutes; EVA 3, Mark C. Lee and Steven L. Smith, 7 hours, 11 minutes; EVA 4, Steven L. Smith, 7 hours, 11 minutes; EVA 4, Steven L. Smith, 7 hours, 11 minutes; EVA 4,

Y-66 Y-66 Y-66 STS-82 Mission Facts (Cont) STS-82 Mission Facts (Cont) STS-82 Mission Facts (Cont) Gregory J. Harbaugh and Joseph R. Tanner, 6 Gregory J. Harbaugh and Joseph R. Tanner, 6 Gregory J. Harbaugh and Joseph R. Tanner, 6 hours, 34 minutes; EVA 5, Mark C. Lee and Steven hours, 34 minutes; EVA 5, Mark C. Lee and Steven hours, 34 minutes; EVA 5, Mark C. Lee and Steven L. Smith, 5 hours, 17 minutes. During EVA 1, Lee L. Smith, 5 hours, 17 minutes. During EVA 1, Lee L. Smith, 5 hours, 17 minutes. During EVA 1, Lee and Smith removed and replaced the Goddard and Smith removed and replaced the Goddard and Smith removed and replaced the Goddard high-resolution spectrograph and the faint-object high-resolution spectrograph and the faint-object high-resolution spectrograph and the faint-object spectrograph with the new space telescope imag- spectrograph with the new space telescope imag- spectrograph with the new space telescope imag- ing spectrograph and the near-infrared camera ing spectrograph and the near-infrared camera ing spectrograph and the near-infrared camera and multiobject spectrometer, respectively. and multiobject spectrometer, respectively. and multiobject spectrometer, respectively. During EVA 2, Harbaugh and Tanner replaced During EVA 2, Harbaugh and Tanner replaced During EVA 2, Harbaugh and Tanner replaced a degraded fine guidance sensor and a failed a degraded fine guidance sensor and a failed a degraded fine guidance sensor and a failed engineering and science tape recorder with new engineering and science tape recorder with new engineering and science tape recorder with new spares. They installed a new unit known as the spares. They installed a new unit known as the spares. They installed a new unit known as the optical control electronics enhancement kit. Dur- optical control electronics enhancement kit. Dur- optical control electronics enhancement kit. Dur- ing EVA 3, Lee and Smith removed and replaced a ing EVA 3, Lee and Smith removed and replaced a ing EVA 3, Lee and Smith removed and replaced a data interface unit and replaced an old reel-to-reel data interface unit and replaced an old reel-to-reel data interface unit and replaced an old reel-to-reel engineering and science tape recorder with a new engineering and science tape recorder with a new engineering and science tape recorder with a new digital solid-state recorder. They also changed digital solid-state recorder. They also changed digital solid-state recorder. They also changed out one of Hubble’s four reaction wheel assem- out one of Hubble’s four reaction wheel assem- out one of Hubble’s four reaction wheel assem- bly units. During EVA 4, Harbaugh and Tanner bly units. During EVA 4, Harbaugh and Tanner bly units. During EVA 4, Harbaugh and Tanner replaced a solar array drive electronics package replaced a solar array drive electronics package replaced a solar array drive electronics package and covers over Hubble’s magnetometers. They and covers over Hubble’s magnetometers. They and covers over Hubble’s magnetometers. They then placed thermal blankets of multilayer material then placed thermal blankets of multilayer material then placed thermal blankets of multilayer material over two areas of degraded insulation around the over two areas of degraded insulation around the over two areas of degraded insulation around the light shield portion of the telescope just below light shield portion of the telescope just below light shield portion of the telescope just below the top of the astronomical observatory. During the top of the astronomical observatory. During the top of the astronomical observatory. During EVA 5, Lee and Smith attached several thermal EVA 5, Lee and Smith attached several thermal EVA 5, Lee and Smith attached several thermal insulation blankets to three equipment compart- insulation blankets to three equipment compart- insulation blankets to three equipment compart- ments at the top of the support systems module ments at the top of the support systems module ments at the top of the support systems module section of Hubble. The compartments contain key section of Hubble. The compartments contain key section of Hubble. The compartments contain key data processing, electronics and scientific instru- data processing, electronics and scientific instru- data processing, electronics and scientific instru- ment telemetry packages. Over the course of the ment telemetry packages. Over the course of the ment telemetry packages. Over the course of the mission, Hubble was also reboosted into an orbit mission, Hubble was also reboosted into an orbit mission, Hubble was also reboosted into an orbit approximately 8 nautical miles higher. approximately 8 nautical miles higher. approximately 8 nautical miles higher.

STS-83 Mission Facts — Columbia — STS-83 Mission Facts — Columbia — STS-83 Mission Facts — Columbia — April 4–8, 1997 April 4–8, 1997 April 4–8, 1997

Commander: James D. Halsell, Jr. Commander: James D. Halsell, Jr. Commander: James D. Halsell, Jr. Pilot: Susan L. Still Pilot: Susan L. Still Pilot: Susan L. Still Payload Commander: Janice Voss Payload Commander: Janice Voss Payload Commander: Janice Voss Mission Specialist: Donald A. Thomas Mission Specialist: Donald A. Thomas Mission Specialist: Donald A. Thomas Mission Specialist: Michael L. Gernhardt Mission Specialist: Michael L. Gernhardt Mission Specialist: Michael L. Gernhardt Payload Specialist: Roger K. Crouch Payload Specialist: Roger K. Crouch Payload Specialist: Roger K. Crouch Payload Specialist: Gregory T. Linteris Payload Specialist: Gregory T. Linteris Payload Specialist: Gregory T. Linteris Mission Duration: 72 hours (3 days), 23 hours, Mission Duration: 72 hours (3 days), 23 hours, Mission Duration: 72 hours (3 days), 23 hours, 13 minutes, 38 seconds 13 minutes, 38 seconds 13 minutes, 38 seconds Miles Traveled: Approximately 1.5 million statute miles Miles Traveled: Approximately 1.5 million statute miles Miles Traveled: Approximately 1.5 million statute miles Inclination: 28.45 degrees Inclination: 28.45 degrees Inclination: 28.45 degrees Orbits of Earth: 63 Orbits of Earth: 63 Orbits of Earth: 63 Orbital Altitude: 160 nautical miles (184 statute miles) Orbital Altitude: 160 nautical miles (184 statute miles) Orbital Altitude: 160 nautical miles (184 statute miles) Landing Touchdown: Approximately 3,174 feet beyond Landing Touchdown: Approximately 3,174 feet beyond Landing Touchdown: Approximately 3,174 feet beyond threshold threshold threshold Landing Rollout: Approximately 8,623 feet Landing Rollout: Approximately 8,623 feet Landing Rollout: Approximately 8,623 feet Y-67 Y-67 Y-67 STS-83 Mission Facts (Cont) STS-83 Mission Facts (Cont) STS-83 Mission Facts (Cont) Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately 213,060 pounds 213,060 pounds 213,060 pounds Lift-off Weight: Approximately 4,523,076 pounds Lift-off Weight: Approximately 4,523,076 pounds Lift-off Weight: Approximately 4,523,076 pounds Orbiter Weight at Lift-off: Approximately 259,927 pounds Orbiter Weight at Lift-off: Approximately 259,927 pounds Orbiter Weight at Lift-off: Approximately 259,927 pounds Landing Speed at Main Gear Touchdown: Approximate- Landing Speed at Main Gear Touchdown: Approximate- Landing Speed at Main Gear Touchdown: Approximate- ly 193 knots (222 miles per hour) ly 193 knots (222 miles per hour) ly 193 knots (222 miles per hour) Payload Weight Up: Approximately 25,530 pounds Payload Weight Up: Approximately 25,530 pounds Payload Weight Up: Approximately 25,530 pounds Payload Weight Down: Approximately 25,530 pounds Payload Weight Down: Approximately 25,530 pounds Payload Weight Down: Approximately 25,530 pounds Landed: Concrete runway 33 at Kennedy Space Center, Landed: Concrete runway 33 at Kennedy Space Center, Landed: Concrete runway 33 at Kennedy Space Center, Florida Florida Florida Payloads: Microgravity Science Laboratory (MSL) 01, Payloads: Microgravity Science Laboratory (MSL) 01, Payloads: Microgravity Science Laboratory (MSL) 01, Spacelab module with long crew transfer tunnel, ex- Spacelab module with long crew transfer tunnel, ex- Spacelab module with long crew transfer tunnel, ex- tended-duration orbiter cryogenic pallet, Cryogenic tended-duration orbiter cryogenic pallet, Cryogenic tended-duration orbiter cryogenic pallet, Cryogenic Flexible Diode Heat Pipe Experiment (CRYOFD), Flexible Diode Heat Pipe Experiment (CRYOFD), Flexible Diode Heat Pipe Experiment (CRYOFD), Orbital Acceleration Research Experiment (OARE), Orbital Acceleration Research Experiment (OARE), Orbital Acceleration Research Experiment (OARE), Protein Crystal Growth (PCG)—Single-Locker Protein Crystal Growth (PCG)—Single-Locker Protein Crystal Growth (PCG)—Single-Locker Thermal Enclosure System (STES), Shuttle Amateur Thermal Enclosure System (STES), Shuttle Amateur Thermal Enclosure System (STES), Shuttle Amateur Radio Experiment (SAREX) II, Midcourse Space Radio Experiment (SAREX) II, Midcourse Space Radio Experiment (SAREX) II, Midcourse Space Experiment (MSX) Experiment (MSX) Experiment (MSX)

The mission was cut short by Shuttle managers due The mission was cut short by Shuttle managers due The mission was cut short by Shuttle managers due to a problem with fuel cell No. 2, which displayed to a problem with fuel cell No. 2, which displayed to a problem with fuel cell No. 2, which displayed evidence of internal voltage degradation after the evidence of internal voltage degradation after the evidence of internal voltage degradation after the launch. launch. launch.

STS-84 Mission Facts — Atlantis — STS-84 Mission Facts — Atlantis — STS-84 Mission Facts — Atlantis — May 15–24, 1997 May 15–24, 1997 May 15–24, 1997

Commander: Charles J. Precourt Commander: Charles J. Precourt Commander: Charles J. Precourt Pilot: Eileen Marie Collins Pilot: Eileen Marie Collins Pilot: Eileen Marie Collins Mission Specialist: Jerry M. Linenger (down only) Mission Specialist: Jerry M. Linenger (down only) Mission Specialist: Jerry M. Linenger (down only) Mission Specialist: C. Michael Foale (up only) Mission Specialist: C. Michael Foale (up only) Mission Specialist: C. Michael Foale (up only) Mission Specialist: Elena V. Kondakova, RSC Energia Mission Specialist: Elena V. Kondakova, RSC Energia Mission Specialist: Elena V. Kondakova, RSC Energia Mission Specialist: Carlos I. Noriega Mission Specialist: Carlos I. Noriega Mission Specialist: Carlos I. Noriega Mission Specialist: Edward T. Lu Mission Specialist: Edward T. Lu Mission Specialist: Edward T. Lu Mission Specialist: Jean-Francois Clervoy, European Mission Specialist: Jean-Francois Clervoy, European Mission Specialist: Jean-Francois Clervoy, European Space Agency Space Agency Space Agency Mission Duration: 216 hours (9 days), 5 hours, 20 min- Mission Duration: 216 hours (9 days), 5 hours, 20 min- Mission Duration: 216 hours (9 days), 5 hours, 20 min- utes, 47 seconds utes, 47 seconds utes, 47 seconds Miles Traveled: Approximately 3.6 million statute miles Miles Traveled: Approximately 3.6 million statute miles Miles Traveled: Approximately 3.6 million statute miles Inclination: 51.6 degrees Inclination: 51.6 degrees Inclination: 51.6 degrees Orbits of Earth: 144 Orbits of Earth: 144 Orbits of Earth: 144 Orbital Altitude: 160 nautical miles (184 statute miles) Orbital Altitude: 160 nautical miles (184 statute miles) Orbital Altitude: 160 nautical miles (184 statute miles) insertion; 213 nautical miles (245 statute miles) for insertion; 213 nautical miles (245 statute miles) for insertion; 213 nautical miles (245 statute miles) for Mir rendezvous Mir rendezvous Mir rendezvous Landing Touchdown: Approximately 3,153 feet beyond Landing Touchdown: Approximately 3,153 feet beyond Landing Touchdown: Approximately 3,153 feet beyond threshold threshold threshold Landing Rollout: Approximately 8,201 feet Landing Rollout: Approximately 8,201 feet Landing Rollout: Approximately 8,201 feet Orbiter Weight at Landing: Approximately 213,865 Orbiter Weight at Landing: Approximately 213,865 Orbiter Weight at Landing: Approximately 213,865 pounds pounds pounds Lift-off Weight: Approximately 4,509,832 pounds Lift-off Weight: Approximately 4,509,832 pounds Lift-off Weight: Approximately 4,509,832 pounds

Y-68 Y-68 Y-68 STS-84 Mission Facts (Cont) STS-84 Mission Facts (Cont) STS-84 Mission Facts (Cont)

Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately 249,624 pounds 249,624 pounds 249,624 pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 210 knots (242 miles per hour) mately 210 knots (242 miles per hour) mately 210 knots (242 miles per hour) Payload Weight Up: Approximately 19,779 pounds Payload Weight Up: Approximately 19,779 pounds Payload Weight Up: Approximately 19,779 pounds Payload Weight Down: Approximately 19,387 pounds Payload Weight Down: Approximately 19,387 pounds Payload Weight Down: Approximately 19,387 pounds Landed: Concrete runway 33 at Kennedy Space Center, Landed: Concrete runway 33 at Kennedy Space Center, Landed: Concrete runway 33 at Kennedy Space Center, Florida Florida Florida Payloads: SPACEHAB 07 double module/Mir 06, Payloads: SPACEHAB 07 double module/Mir 06, Payloads: SPACEHAB 07 double module/Mir 06, transfer tunnel, transfer tunnel extension, orbiter transfer tunnel, transfer tunnel extension, orbiter transfer tunnel, transfer tunnel extension, orbiter docking system, European Space Agency proxim- docking system, European Space Agency proxim- docking system, European Space Agency proxim- ity operations sensor (EPS), Shuttle/Mir Mission 06 ity operations sensor (EPS), Shuttle/Mir Mission 06 ity operations sensor (EPS), Shuttle/Mir Mission 06 middeck science, Cosmic Radiation Effects and middeck science, Cosmic Radiation Effects and middeck science, Cosmic Radiation Effects and Activation Monitor (CREAM), Radia tion Monitoring Activation Monitor (CREAM), Radia tion Monitoring Activation Monitor (CREAM), Radia tion Monitoring Equipment (RME) III, Shuttle Ionospheric Modifica- Equipment (RME) III, Shuttle Ionospheric Modifica- Equipment (RME) III, Shuttle Ionospheric Modifica- tion With Pulsed Local Exhaust (SIMPLEX) Liquid tion With Pulsed Local Exhaust (SIMPLEX) Liquid tion With Pulsed Local Exhaust (SIMPLEX) Liquid Motion Experiment (LME), Protein Crystal Growth Motion Experiment (LME), Protein Crystal Growth Motion Experiment (LME), Protein Crystal Growth (PCG)—Single-Locker Thermal Enclosure System (PCG)—Single-Locker Thermal Enclosure System (PCG)—Single-Locker Thermal Enclosure System (STES), Midcourse Space Experiment (MSX), (STES), Midcourse Space Experiment (MSX), (STES), Midcourse Space Experiment (MSX), Electrolysis Performance Improvement Concept Electrolysis Performance Improvement Concept Electrolysis Performance Improvement Concept Study (EPICS) Study (EPICS) Study (EPICS) STS-94 Mission Facts — Columbia — STS-94 Mission Facts — Columbia — STS-94 Mission Facts — Columbia — July 1–17, 1997 July 1–17, 1997 July 1–17, 1997

Commander: James D. Halsell, Jr. Commander: James D. Halsell, Jr. Commander: James D. Halsell, Jr. Pilot: Susan L. Still Pilot: Susan L. Still Pilot: Susan L. Still Mission Specialist: Donald A. Thomas Mission Specialist: Donald A. Thomas Mission Specialist: Donald A. Thomas Mission Specialist: Janice Voss Mission Specialist: Janice Voss Mission Specialist: Janice Voss Mission Specialist: Michael L. Gernhardt Mission Specialist: Michael L. Gernhardt Mission Specialist: Michael L. Gernhardt Payload Specialist: Gregory T. Linteris Payload Specialist: Gregory T. Linteris Payload Specialist: Gregory T. Linteris Payload Specialist: Roger K. Crouch Payload Specialist: Roger K. Crouch Payload Specialist: Roger K. Crouch Mission Duration: 360 hours (15 days), 16 hours, Mission Duration: 360 hours (15 days), 16 hours, Mission Duration: 360 hours (15 days), 16 hours, 45 minutes, 29 seconds 45 minutes, 29 seconds 45 minutes, 29 seconds Miles Traveled: Approximately 6.2 million statute miles Miles Traveled: Approximately 6.2 million statute miles Miles Traveled: Approximately 6.2 million statute miles Inclination: 28.45 degrees Inclination: 28.45 degrees Inclination: 28.45 degrees Orbits of Earth: 251 Orbits of Earth: 251 Orbits of Earth: 251 Orbital Altitude: 160 nautical miles (184 statute miles) Orbital Altitude: 160 nautical miles (184 statute miles) Orbital Altitude: 160 nautical miles (184 statute miles) Landing Touchdown: Approximately 3,133 feet beyond Landing Touchdown: Approximately 3,133 feet beyond Landing Touchdown: Approximately 3,133 feet beyond threshold threshold threshold Landing Rollout: Approximately 8,910 feet Landing Rollout: Approximately 8,910 feet Landing Rollout: Approximately 8,910 feet Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately 230,292 pounds 230,292 pounds 230,292 pounds Lift-off Weight: Approximately 4,523,389 pounds Lift-off Weight: Approximately 4,523,389 pounds Lift-off Weight: Approximately 4,523,389 pounds Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately 260,266 pounds 260,266 pounds 260,266 pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 208 knots (239 miles per hour) mately 208 knots (239 miles per hour) mately 208 knots (239 miles per hour) Payload Weight Up: Approximately 25,568 pounds Payload Weight Up: Approximately 25,568 pounds Payload Weight Up: Approximately 25,568 pounds Payload Weight Down: Approximately 25,568 pounds Payload Weight Down: Approximately 25,568 pounds Payload Weight Down: Approximately 25,568 pounds

Y-69 Y-69 Y-69 STS-94 Mission Facts (Cont) STS-94 Mission Facts (Cont) STS-94 Mission Facts (Cont) Landed: Concrete runway 33 at Kennedy Space Center, Landed: Concrete runway 33 at Kennedy Space Center, Landed: Concrete runway 33 at Kennedy Space Center, Florida Florida Florida Payloads: First Microgravity Science Laboratory (MSL) Payloads: First Microgravity Science Laboratory (MSL) Payloads: First Microgravity Science Laboratory (MSL) 01; Spacelab module with long crew transfer tun- 01; Spacelab module with long crew transfer tun- 01; Spacelab module with long crew transfer tun- nel; Extended-Duration Orbiter Cryogenic Pallet; nel; Extended-Duration Orbiter Cryogenic Pallet; nel; Extended-Duration Orbiter Cryogenic Pallet; Cryogenic Flexible Diode Heat Pipe Experiment Cryogenic Flexible Diode Heat Pipe Experiment Cryogenic Flexible Diode Heat Pipe Experiment (CRYOFD); Orbiter Acceleration Research Experi- (CRYOFD); Orbiter Acceleration Research Experi- (CRYOFD); Orbiter Acceleration Research Experi- ment (OARE); Protein Crystal Growth (PCG)—Sin- ment (OARE); Protein Crystal Growth (PCG)—Sin- ment (OARE); Protein Crystal Growth (PCG)—Sin- gle-Locker Thermal Enclosure System (STES); gle-Locker Thermal Enclosure System (STES); gle-Locker Thermal Enclosure System (STES); Shuttle Amateur Radio Experiment (SAREX) II; Shuttle Amateur Radio Experiment (SAREX) II; Shuttle Amateur Radio Experiment (SAREX) II; Midcourse Space Experiment (MSX)—payload of Midcourse Space Experiment (MSX)—payload of Midcourse Space Experiment (MSX)—payload of opportunity with no onboard hardware opportunity with no onboard hardware opportunity with no onboard hardware

STS-85 Mission Facts — Discovery— STS-85 Mission Facts — Discovery— STS-85 Mission Facts — Discovery— August 7–19, 1997 August 7–19, 1997 August 7–19, 1997

Commander: Curtis L. Brown, Jr. Commander: Curtis L. Brown, Jr. Commander: Curtis L. Brown, Jr. Pilot: Kent Rominger Pilot: Kent Rominger Pilot: Kent Rominger Mission Specialist: N. Jan Davis Mission Specialist: N. Jan Davis Mission Specialist: N. Jan Davis Mission Specialist: Robert L. Curbeam, Jr. Mission Specialist: Robert L. Curbeam, Jr. Mission Specialist: Robert L. Curbeam, Jr. Mission Specialist: Stephen K. Robinson Mission Specialist: Stephen K. Robinson Mission Specialist: Stephen K. Robinson Payload Specialist: Bjarni Tryggvason, Canadian Space Payload Specialist: Bjarni Tryggvason, Canadian Space Payload Specialist: Bjarni Tryggvason, Canadian Space Agency Agency Agency Mission Duration: 264 hours (11 days), 20 hours, 28 Mission Duration: 264 hours (11 days), 20 hours, 28 Mission Duration: 264 hours (11 days), 20 hours, 28 minutes, 7 seconds minutes, 7 seconds minutes, 7 seconds Miles Traveled: Approximately 4.7 million statute miles Miles Traveled: Approximately 4.7 million statute miles Miles Traveled: Approximately 4.7 million statute miles Inclination: 57 degrees Inclination: 57 degrees Inclination: 57 degrees Orbits of Earth: 190 Orbits of Earth: 190 Orbits of Earth: 190 Orbital Altitude: 160 nautical miles (184 statute miles) Orbital Altitude: 160 nautical miles (184 statute miles) Orbital Altitude: 160 nautical miles (184 statute miles) Landing Touchdown: Approximately 3,074 feet beyond Landing Touchdown: Approximately 3,074 feet beyond Landing Touchdown: Approximately 3,074 feet beyond threshold threshold threshold Landing Rollout: Approximately 8,745 feet Landing Rollout: Approximately 8,745 feet Landing Rollout: Approximately 8,745 feet Orbiter Weight at Landing: Approximately 219,571 Orbiter Weight at Landing: Approximately 219,571 Orbiter Weight at Landing: Approximately 219,571 pounds pounds pounds Lift-off Weight: Approximately 4,512,125 pounds Lift-off Weight: Approximately 4,512,125 pounds Lift-off Weight: Approximately 4,512,125 pounds Orbiter Weight at Lift-off: Approximately 250,101 Orbiter Weight at Lift-off: Approximately 250,101 Orbiter Weight at Lift-off: Approximately 250,101 pounds pounds pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 185 knots (213 miles per hour) mately 185 knots (213 miles per hour) mately 185 knots (213 miles per hour) Payload Weight Up: Approximately 24,982 pounds Payload Weight Up: Approximately 24,982 pounds Payload Weight Up: Approximately 24,982 pounds Payload Weight Down: Approximately 24,843 pounds Payload Weight Down: Approximately 24,843 pounds Payload Weight Down: Approximately 24,843 pounds Landed: Concrete runway 33 at Kennedy Space Center, Landed: Concrete runway 33 at Kennedy Space Center, Landed: Concrete runway 33 at Kennedy Space Center, Florida Florida Florida Payloads: Cryogenic Infrared Spectrometers and Payloads: Cryogenic Infrared Spectrometers and Payloads: Cryogenic Infrared Spectrometers and Telescopes for the Atmosphere (CRISTA)—Shuttle Telescopes for the Atmosphere (CRISTA)—Shuttle Telescopes for the Atmosphere (CRISTA)—Shuttle Pallet Satellite (SPAS) II; International Extreme Pallet Satellite (SPAS) II; International Extreme Pallet Satellite (SPAS) II; International Extreme Ultraviolet Hitchhiker (IEH) 02; Manipulator Flight Ultraviolet Hitchhiker (IEH) 02; Manipulator Flight Ultraviolet Hitchhiker (IEH) 02; Manipulator Flight Demonstration (MFD); Technology Applications Demonstration (MFD); Technology Applications Demonstration (MFD); Technology Applications and Science (TAS) 01; Getaway Specials 572 and and Science (TAS) 01; Getaway Specials 572 and and Science (TAS) 01; Getaway Specials 572 and 745; MFD aft flight deck equipment; Bioreactor 745; MFD aft flight deck equipment; Bioreactor 745; MFD aft flight deck equipment; Bioreactor

Y-70 Y-70 Y-70 STS-85 Mission Facts (Cont) STS-85 Mission Facts (Cont) STS-85 Mission Facts (Cont) Demonstration System (BDS) 03, Configuration B; Demonstration System (BDS) 03, Configuration B; Demonstration System (BDS) 03, Configuration B; Biological Research in Canisters (BRIC) 10; Shuttle Biological Research in Canisters (BRIC) 10; Shuttle Biological Research in Canisters (BRIC) 10; Shuttle Ionospheric Modification With Pulsed Local Exhaust Ionospheric Modification With Pulsed Local Exhaust Ionospheric Modification With Pulsed Local Exhaust (SIMPLEX); Protein Crystal Growth (PCG)—Single- (SIMPLEX); Protein Crystal Growth (PCG)—Single- (SIMPLEX); Protein Crystal Growth (PCG)—Single- Locker Thermal Enclosure System (STES) 05; Locker Thermal Enclosure System (STES) 05; Locker Thermal Enclosure System (STES) 05; Advanced X-Ray Astrophysics Facility—Imaging Advanced X-Ray Astrophysics Facility—Imaging Advanced X-Ray Astrophysics Facility—Imaging (AXAF) Charge Coupled Device (CCD) Imaging (AXAF) Charge Coupled Device (CCD) Imaging (AXAF) Charge Coupled Device (CCD) Imaging Spectrometer (ACIS); Midcourse Space Experiment Spectrometer (ACIS); Midcourse Space Experiment Spectrometer (ACIS); Midcourse Space Experiment (MSX)—payload of opportunity with no onboard (MSX)—payload of opportunity with no onboard (MSX)—payload of opportunity with no onboard hardware; Southwest Ultraviolet Imaging System hardware; Southwest Ultraviolet Imaging System hardware; Southwest Ultraviolet Imaging System (SWIS); Solid Surface Combustion Experiment (SWIS); Solid Surface Combustion Experiment (SWIS); Solid Surface Combustion Experiment (SSCE) (SSCE) (SSCE)

STS-86 Mission Facts – Atlantis – STS-86 Mission Facts – Atlantis – STS-86 Mission Facts – Atlantis – September 25–October 6, 1997 September 25–October 6, 1997 September 25–October 6, 1997

Commander: James D. Wetherbee Commander: James D. Wetherbee Commander: James D. Wetherbee Pilot: Michael J. Bloomfield Pilot: Michael J. Bloomfield Pilot: Michael J. Bloomfield Mission Specialist: Vladimir Georgievich Titov, Russian Mission Specialist: Vladimir Georgievich Titov, Russian Mission Specialist: Vladimir Georgievich Titov, Russian Space Agency Space Agency Space Agency Mission Specialist: Scott E. Parazynski Mission Specialist: Scott E. Parazynski Mission Specialist: Scott E. Parazynski Mission Specialist: Jean-Loup J. M. Chretien, French Mission Specialist: Jean-Loup J. M. Chretien, French Mission Specialist: Jean-Loup J. M. Chretien, French Space Agency Space Agency Space Agency Mission Specialist: Wendy B. Lawrence Mission Specialist: Wendy B. Lawrence Mission Specialist: Wendy B. Lawrence Mission Specialist: David A. Wolf—up only Mission Specialist: David A. Wolf—up only Mission Specialist: David A. Wolf—up only Mission Specialist: C. Michael Foale—down only Mission Specialist: C. Michael Foale—down only Mission Specialist: C. Michael Foale—down only Mission Duration: 240 hours (10 days), 19 hours, Mission Duration: 240 hours (10 days), 19 hours, Mission Duration: 240 hours (10 days), 19 hours, 22 minutes, 12 seconds 22 minutes, 12 seconds 22 minutes, 12 seconds Miles Traveled: Approximately 4,225,000 statute miles Miles Traveled: Approximately 4,225,000 statute miles Miles Traveled: Approximately 4,225,000 statute miles Inclination: 51.6 degrees Inclination: 51.6 degrees Inclination: 51.6 degrees Orbits of Earth: 170 Orbits of Earth: 170 Orbits of Earth: 170 Orbital Altitude: 160 nautical miles (184 statute miles) Orbital Altitude: 160 nautical miles (184 statute miles) Orbital Altitude: 160 nautical miles (184 statute miles) at insertion; 213 nautical miles (245 statute miles) at insertion; 213 nautical miles (245 statute miles) at insertion; 213 nautical miles (245 statute miles) for Mir rendezvous for Mir rendezvous for Mir rendezvous Landing Touchdown: Approximately 2,490 feet beyond Landing Touchdown: Approximately 2,490 feet beyond Landing Touchdown: Approximately 2,490 feet beyond threshold threshold threshold Landing Rollout: Approximately 11,956 feet Landing Rollout: Approximately 11,956 feet Landing Rollout: Approximately 11,956 feet Orbit Weight at Landing: Approximately Orbit Weight at Landing: Approximately Orbit Weight at Landing: Approximately 213,979 pounds 213,979 pounds 213,979 pounds Lift-off Weight: Approximately 4,514,278 pounds Lift-off Weight: Approximately 4,514,278 pounds Lift-off Weight: Approximately 4,514,278 pounds Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately 251,518 pounds 251,518 pounds 251,518 pounds Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 198 knots (228 miles per hour) mately 198 knots (228 miles per hour) mately 198 knots (228 miles per hour) Payload Weight Up: Approximately 20,531 pounds Payload Weight Up: Approximately 20,531 pounds Payload Weight Up: Approximately 20,531 pounds Payload Weight Down: Approximately 20,079 pounds Payload Weight Down: Approximately 20,079 pounds Payload Weight Down: Approximately 20,079 pounds Landed: Concrete runway 15 at Kennedy Space Center, Landed: Concrete runway 15 at Kennedy Space Center, Landed: Concrete runway 15 at Kennedy Space Center, Florida Florida Florida Payloads: SPACEHAB double module/Mir 07; transfer Payloads: SPACEHAB double module/Mir 07; transfer Payloads: SPACEHAB double module/Mir 07; transfer tunnel; transfer tunnel extension; orbiter docking tunnel; transfer tunnel extension; orbiter docking tunnel; transfer tunnel extension; orbiter docking system; RME1314: European Space Agency Prox- system; RME1314: European Space Agency Prox- system; RME1314: European Space Agency Prox- imity Operations Sensor (EPS); Seeds in imity Operations Sensor (EPS); Seeds in imity Operations Sensor (EPS); Seeds in

Y-71 Y-71 Y-71 STS-86 Mission Facts (Cont) STS-86 Mission Facts (Cont) STS-86 Mission Facts (Cont) Space (SEEDS) II; MEEP carriers; Shuttle/Mir Space (SEEDS) II; MEEP carriers; Shuttle/Mir Space (SEEDS) II; MEEP carriers; Shuttle/Mir Mission 07 middeck science; Cosmic Radiation Mission 07 middeck science; Cosmic Radiation Mission 07 middeck science; Cosmic Radiation Effects and Activation Monitor (CREAM); Effects and Activation Monitor (CREAM); Effects and Activation Monitor (CREAM); KidSat; Commercial Protein Crystal Growth KidSat; Commercial Protein Crystal Growth KidSat; Commercial Protein Crystal Growth (CPCG); Cell Culture Module (CCM) A; Risk Mitiga- (CPCG); Cell Culture Module (CCM) A; Risk Mitiga- (CPCG); Cell Culture Module (CCM) A; Risk Mitiga- tion Experiments tion Experiments tion Experiments Extravehicular Activity (EVA): Scott E. Parazynski and Extravehicular Activity (EVA): Scott E. Parazynski and Extravehicular Activity (EVA): Scott E. Parazynski and Vladimir Georgievich Titov, Russian Space Agency, Vladimir Georgievich Titov, Russian Space Agency, Vladimir Georgievich Titov, Russian Space Agency, 5 hours, 1 minute. During this first U.S. spacewalk 5 hours, 1 minute. During this first U.S. spacewalk 5 hours, 1 minute. During this first U.S. spacewalk to include participation by a foreign astronaut, to include participation by a foreign astronaut, to include participation by a foreign astronaut, Parazynski and Titov retrieved MEEP and tested Parazynski and Titov retrieved MEEP and tested Parazynski and Titov retrieved MEEP and tested hardware for future EVA activities, including an hardware for future EVA activities, including an hardware for future EVA activities, including an evaluation of the Simplified Aid for EVA Rescue evaluation of the Simplified Aid for EVA Rescue evaluation of the Simplified Aid for EVA Rescue (SAFER), a small jet-backpack designed for use as (SAFER), a small jet-backpack designed for use as (SAFER), a small jet-backpack designed for use as a type of life jacket during station assembly. They a type of life jacket during station assembly. They a type of life jacket during station assembly. They also retrieved a solar array cap to be placed on also retrieved a solar array cap to be placed on also retrieved a solar array cap to be placed on the damaged Spektr module to the exterior of the the damaged Spektr module to the exterior of the the damaged Spektr module to the exterior of the docking module. docking module. docking module.

STS-87 Mission Facts — Columbia — STS-87 Mission Facts — Columbia — STS-87 Mission Facts — Columbia — November 19–December 5, 1997 November 19–December 5, 1997 November 19–December 5, 1997

Commander: Kevin R. Kregel Commander: Kevin R. Kregel Commander: Kevin R. Kregel Pilot: Steven W. Lindsey Pilot: Steven W. Lindsey Pilot: Steven W. Lindsey Mission Specialist: Kalpona Chawla Mission Specialist: Kalpona Chawla Mission Specialist: Kalpona Chawla Mission Specialist: Winston E. Scott Mission Specialist: Winston E. Scott Mission Specialist: Winston E. Scott Mission Specialist: Takao Doi, National Space Devel- Mission Specialist: Takao Doi, National Space Devel- Mission Specialist: Takao Doi, National Space Devel- opment Agency of Japan opment Agency of Japan opment Agency of Japan Payload Specialist: Leonid Kadenyuk, National Space Payload Specialist: Leonid Kadenyuk, National Space Payload Specialist: Leonid Kadenyuk, National Space Agency of Ukraine Agency of Ukraine Agency of Ukraine Mission Duration: 360 hours (15 days), 16 hours, Mission Duration: 360 hours (15 days), 16 hours, Mission Duration: 360 hours (15 days), 16 hours, 35 minutes, 1 second 35 minutes, 1 second 35 minutes, 1 second Miles Traveled: Approximately 6.5 million statute miles Miles Traveled: Approximately 6.5 million statute miles Miles Traveled: Approximately 6.5 million statute miles Inclination: 28.45 degrees Inclination: 28.45 degrees Inclination: 28.45 degrees Orbits of Earth: 252 Orbits of Earth: 252 Orbits of Earth: 252 Orbital Altitude: 150 nautical miles (173 statute miles) Orbital Altitude: 150 nautical miles (173 statute miles) Orbital Altitude: 150 nautical miles (173 statute miles) Landing Touchdown: Approximately 2,635 feet beyond Landing Touchdown: Approximately 2,635 feet beyond Landing Touchdown: Approximately 2,635 feet beyond threshold threshold threshold Landing Rollout: Approximately 8,003 feet Landing Rollout: Approximately 8,003 feet Landing Rollout: Approximately 8,003 feet Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately 231,625 pounds 231,625 pounds 231,625 pounds Lift-off Weight: Approximately 4,523,442 pounds Lift-off Weight: Approximately 4,523,442 pounds Lift-off Weight: Approximately 4,523,442 pounds Orbiter Weight at Lift-off: Approximately 260,799 pounds Orbiter Weight at Lift-off: Approximately 260,799 pounds Orbiter Weight at Lift-off: Approximately 260,799 pounds Landing Speed at Main Gear Touchdown: Approximate- Landing Speed at Main Gear Touchdown: Approximate- Landing Speed at Main Gear Touchdown: Approximate- ly 188 knots (216 miles per hour) ly 188 knots (216 miles per hour) ly 188 knots (216 miles per hour) Payload Weight Up: Approximately 22,130 pounds Payload Weight Up: Approximately 22,130 pounds Payload Weight Up: Approximately 22,130 pounds Payload Weight Down: Approximately 22,130 pounds Payload Weight Down: Approximately 22,130 pounds Payload Weight Down: Approximately 22,130 pounds Landed: Concrete runway 33 at Kennedy Space Center, Landed: Concrete runway 33 at Kennedy Space Center, Landed: Concrete runway 33 at Kennedy Space Center, Florida Florida Florida Payloads: Shuttle Pointed Autonomous Research Tool Payloads: Shuttle Pointed Autonomous Research Tool Payloads: Shuttle Pointed Autonomous Research Tool for Astronomy (SPARTAN) 201-04; United States for Astronomy (SPARTAN) 201-04; United States for Astronomy (SPARTAN) 201-04; United States Microgravity Payload (SMP) 4; Extravehicular Microgravity Payload (SMP) 4; Extravehicular Microgravity Payload (SMP) 4; Extravehicular

Y-72 Y-72 Y-72 STS-87 Mission Facts (Cont) STS-87 Mission Facts (Cont) STS-87 Mission Facts (Cont) Activity (EVA) Demonstration Flight Test (EDFT) Activity (EVA) Demonstration Flight Test (EDFT) Activity (EVA) Demonstration Flight Test (EDFT) 05; Shuttle Ozone Limb Sounding Experiment 05; Shuttle Ozone Limb Sounding Experiment 05; Shuttle Ozone Limb Sounding Experiment (SOLSE); Loop Heat Pipe (LHP); Sodium Sulfur (SOLSE); Loop Heat Pipe (LHP); Sodium Sulfur (SOLSE); Loop Heat Pipe (LHP); Sodium Sulfur Battery Experiment (NaSBE); Turbulent Gas Jet Battery Experiment (NaSBE); Turbulent Gas Jet Battery Experiment (NaSBE); Turbulent Gas Jet Diffusion Flames (TGDF); Getaway Special (GAS) Diffusion Flames (TGDF); Getaway Special (GAS) Diffusion Flames (TGDF); Getaway Special (GAS) 036; Shuttle Ionospheric Modification With Pulsed 036; Shuttle Ionospheric Modification With Pulsed 036; Shuttle Ionospheric Modification With Pulsed Local Exhaust (SIMPLEX); Collaborative Ukraine Local Exhaust (SIMPLEX); Collaborative Ukraine Local Exhaust (SIMPLEX); Collaborative Ukraine Experiment (CUE); Autonomous EVA Robotic Experiment (CUE); Autonomous EVA Robotic Experiment (CUE); Autonomous EVA Robotic (AER) Camera/Sprint; Midcourse Space Experi- (AER) Camera/Sprint; Midcourse Space Experi- (AER) Camera/Sprint; Midcourse Space Experi- ment (MSX) ment (MSX) ment (MSX) Extravehicular Activity (EVA): EVA 1, Winston Scott Extravehicular Activity (EVA): EVA 1, Winston Scott Extravehicular Activity (EVA): EVA 1, Winston Scott and Takao Doi, 7 hours, 43 minutes; EVA 2, Win- and Takao Doi, 7 hours, 43 minutes; EVA 2, Win- and Takao Doi, 7 hours, 43 minutes; EVA 2, Win- ston Scott and Takao Doi, 4 hours, 59 minutes, 40 ston Scott and Takao Doi, 4 hours, 59 minutes, 40 ston Scott and Takao Doi, 4 hours, 59 minutes, 40 seconds. During EVA 1, Scott and Doi manually seconds. During EVA 1, Scott and Doi manually seconds. During EVA 1, Scott and Doi manually captured the SPARTAN satellite, whose attitude captured the SPARTAN satellite, whose attitude captured the SPARTAN satellite, whose attitude control system had failed following its release from control system had failed following its release from control system had failed following its release from Columbia's robot arm on November 21. The two Columbia's robot arm on November 21. The two Columbia's robot arm on November 21. The two also evaluated equipment and procedures that also evaluated equipment and procedures that also evaluated equipment and procedures that will be used with future International Space Station will be used with future International Space Station will be used with future International Space Station operations. During EVA 2, Scott and Doi complet- operations. During EVA 2, Scott and Doi complet- operations. During EVA 2, Scott and Doi complet- ed tasks originally planned for the mission's first ed tasks originally planned for the mission's first ed tasks originally planned for the mission's first spacewalk. They also used the SPARTAN satellite spacewalk. They also used the SPARTAN satellite spacewalk. They also used the SPARTAN satellite as a laser target to prepare for future automatic as a laser target to prepare for future automatic as a laser target to prepare for future automatic spacecraft dockings. In addition, they tested the spacecraft dockings. In addition, they tested the spacecraft dockings. In addition, they tested the AER Camera/Sprint, a free-flying video camera AER Camera/Sprint, a free-flying video camera AER Camera/Sprint, a free-flying video camera designed to perform remote inspections of the designed to perform remote inspections of the designed to perform remote inspections of the Shuttle or station. Shuttle or station. Shuttle or station.

STS-89 Mission Facts — Endeavour — STS-89 Mission Facts — Endeavour — STS-89 Mission Facts — Endeavour — January 22–31, 1998 January 22–31, 1998 January 22–31, 1998

Commander: Terrence W. Wilcutt Commander: Terrence W. Wilcutt Commander: Terrence W. Wilcutt Pilot: Joe Frank Edwards, Jr. Pilot: Joe Frank Edwards, Jr. Pilot: Joe Frank Edwards, Jr. Mission Specialist: James F. Reilly, II Mission Specialist: James F. Reilly, II Mission Specialist: James F. Reilly, II Mission Specialist: Michael P. Anderson Mission Specialist: Michael P. Anderson Mission Specialist: Michael P. Anderson Mission Specialist/Payload Commander: Mission Specialist/Payload Commander: Mission Specialist/Payload Commander: Bonnie J. Dunbar Bonnie J. Dunbar Bonnie J. Dunbar Mission Specialist: Salizhan Shakirovich Sharipov, Mission Specialist: Salizhan Shakirovich Sharipov, Mission Specialist: Salizhan Shakirovich Sharipov, Russian Space Agency Russian Space Agency Russian Space Agency Mission Specialist: Andrew S.W. Thomas Mission Specialist: Andrew S.W. Thomas Mission Specialist: Andrew S.W. Thomas Mission Specialist: David A. Wolf Mission Specialist: David A. Wolf Mission Specialist: David A. Wolf Mission Duration: 192 hours (8 days), 19 hours, Mission Duration: 192 hours (8 days), 19 hours, Mission Duration: 192 hours (8 days), 19 hours, 48 minutes, 4 seconds 48 minutes, 4 seconds 48 minutes, 4 seconds Miles Traveled: Approximately 3.6 million statute miles Miles Traveled: Approximately 3.6 million statute miles Miles Traveled: Approximately 3.6 million statute miles Inclination: 51.6 degrees Inclination: 51.6 degrees Inclination: 51.6 degrees Orbits of Earth: 139 Orbits of Earth: 139 Orbits of Earth: 139 Orbital Altitude: 160 nautical miles (184 statute miles) Orbital Altitude: 160 nautical miles (184 statute miles) Orbital Altitude: 160 nautical miles (184 statute miles) at insertion; 213 nautical miles (245 statute miles) at insertion; 213 nautical miles (245 statute miles) at insertion; 213 nautical miles (245 statute miles) for Mir rendezvous for Mir rendezvous for Mir rendezvous Landing Touchdown: Approximately 2,796 feet beyond Landing Touchdown: Approximately 2,796 feet beyond Landing Touchdown: Approximately 2,796 feet beyond threshold threshold threshold Landing Rollout: Approximately 9,769 feet Landing Rollout: Approximately 9,769 feet Landing Rollout: Approximately 9,769 feet Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately 216,241 pounds 216,241 pounds 216,241 pounds Y-73 Y-73 Y-73 STS-89 Mission Facts (Cont) STS-89 Mission Facts (Cont) STS-89 Mission Facts (Cont) Lift-off Weight: Approximately 4,512,608 pounds Lift-off Weight: Approximately 4,512,608 pounds Lift-off Weight: Approximately 4,512,608 pounds Orbiter Weight at Lift-off: Approximately 251,692 pounds Orbiter Weight at Lift-off: Approximately 251,692 pounds Orbiter Weight at Lift-off: Approximately 251,692 pounds Landing Speed at Main Gear Touchdown: Approximate- Landing Speed at Main Gear Touchdown: Approximate- Landing Speed at Main Gear Touchdown: Approximate- ly 202 knots (232 miles per hour) ly 202 knots (232 miles per hour) ly 202 knots (232 miles per hour) Payload Weight Up: Approximately 21,940 pounds Payload Weight Up: Approximately 21,940 pounds Payload Weight Up: Approximately 21,940 pounds Payload Weight Down: Approximately 19,529 pounds Payload Weight Down: Approximately 19,529 pounds Payload Weight Down: Approximately 19,529 pounds Landed: Concrete runway 15 at Kennedy Space Center, Landed: Concrete runway 15 at Kennedy Space Center, Landed: Concrete runway 15 at Kennedy Space Center, Florida Florida Florida Payloads: SPACEHAB 08 double module/Mir 08; transfer Payloads: SPACEHAB 08 double module/Mir 08; transfer Payloads: SPACEHAB 08 double module/Mir 08; transfer tunnel; transfer tunnel extension; orbiter dock- tunnel; transfer tunnel extension; orbiter dock- tunnel; transfer tunnel extension; orbiter dock- ing system; Getaway Specials 093, 141, 145, and ing system; Getaway Specials 093, 141, 145, and ing system; Getaway Specials 093, 141, 145, and 432; Phase 1 requirements (Shuttle/Mir Mission 432; Phase 1 requirements (Shuttle/Mir Mission 432; Phase 1 requirements (Shuttle/Mir Mission 08 middeck science, mission support equipment 08 middeck science, mission support equipment 08 middeck science, mission support equipment and risk mitigation experiments); cosmic radiation and risk mitigation experiments); cosmic radiation and risk mitigation experiments); cosmic radiation effects and activation monitor (CREAM); Shuttle effects and activation monitor (CREAM); Shuttle effects and activation monitor (CREAM); Shuttle ionospheric modification with pulsed local exhaust ionospheric modification with pulsed local exhaust ionospheric modification with pulsed local exhaust (SIMPLEX) payload of opportunity; EarthKAM (also (SIMPLEX) payload of opportunity; EarthKAM (also (SIMPLEX) payload of opportunity; EarthKAM (also known as KidSat); microgravity plant nutrient experi- known as KidSat); microgravity plant nutrient experi- known as KidSat); microgravity plant nutrient experi- ment (MPNE); human performance (HP) experi- ment (MPNE); human performance (HP) experi- ment (MPNE); human performance (HP) experi- ment; closed equilibrated biological aquatic system ment; closed equilibrated biological aquatic system ment; closed equilibrated biological aquatic system (CEBAS); DTOs; and DSOs (CEBAS); DTOs; and DSOs (CEBAS); DTOs; and DSOs STS-90 Mission Facts — Columbia — STS-90 Mission Facts — Columbia — STS-90 Mission Facts — Columbia — April 17–May 3, 1998 April 17–May 3, 1998 April 17–May 3, 1998

Commander: Richard A. Searfoss Commander: Richard A. Searfoss Commander: Richard A. Searfoss Pilot: Scott D. Altman Pilot: Scott D. Altman Pilot: Scott D. Altman Mission Specialist: Kathryn “Kay” Hire Mission Specialist: Kathryn “Kay” Hire Mission Specialist: Kathryn “Kay” Hire Mission Specialist: Richard M. Linnehan Mission Specialist: Richard M. Linnehan Mission Specialist: Richard M. Linnehan Mission Specialist: Dafydd (Dave) Rhys Williams, Mission Specialist: Dafydd (Dave) Rhys Williams, Mission Specialist: Dafydd (Dave) Rhys Williams, Canadian Space Agency Canadian Space Agency Canadian Space Agency Payload Specialist: Dr. Jay C. Buckey Payload Specialist: Dr. Jay C. Buckey Payload Specialist: Dr. Jay C. Buckey Payload Specialist: Dr. James A. Pawelczyk Payload Specialist: Dr. James A. Pawelczyk Payload Specialist: Dr. James A. Pawelczyk Mission Duration: 360 hours (15 days), 21 hours, Mission Duration: 360 hours (15 days), 21 hours, Mission Duration: 360 hours (15 days), 21 hours, 50 minutes, 58 seconds 50 minutes, 58 seconds 50 minutes, 58 seconds Miles Traveled: Approximately 6.375 million statute Miles Traveled: Approximately 6.375 million statute Miles Traveled: Approximately 6.375 million statute miles miles miles Inclination: 39 degrees Inclination: 39 degrees Inclination: 39 degrees Orbits of Earth: 256 Orbits of Earth: 256 Orbits of Earth: 256 Orbital Altitude: 150 nautical miles (173 statute miles) Orbital Altitude: 150 nautical miles (173 statute miles) Orbital Altitude: 150 nautical miles (173 statute miles) Landing Touchdown: Approximately 1,694 feet beyond Landing Touchdown: Approximately 1,694 feet beyond Landing Touchdown: Approximately 1,694 feet beyond threshold threshold threshold Landing Rollout: Approximately 9,949 feet Landing Rollout: Approximately 9,949 feet Landing Rollout: Approximately 9,949 feet Orbiter Weight at Landing: Approximately 231,113 Orbiter Weight at Landing: Approximately 231,113 Orbiter Weight at Landing: Approximately 231,113 pounds pounds pounds Lift-off Weight: Approximately 4,523,770 pounds Lift-off Weight: Approximately 4,523,770 pounds Lift-off Weight: Approximately 4,523,770 pounds Orbiter Weight at Lift-off: Approximately 262,357 pounds Orbiter Weight at Lift-off: Approximately 262,357 pounds Orbiter Weight at Lift-off: Approximately 262,357 pounds Landing Speed at Main Gear Touchdown: Approximate- Landing Speed at Main Gear Touchdown: Approximate- Landing Speed at Main Gear Touchdown: Approximate- ly 224 knots (258 miles per hour) ly 224 knots (258 miles per hour) ly 224 knots (258 miles per hour) Payload Weight Up: Approximately 26,150 pounds Payload Weight Up: Approximately 26,150 pounds Payload Weight Up: Approximately 26,150 pounds Payload Weight Down: Approximately 26,150 pounds Payload Weight Down: Approximately 26,150 pounds Payload Weight Down: Approximately 26,150 pounds

Y-74 Y-74 Y-74 STS-90 Mission Facts (Cont) STS-90 Mission Facts (Cont) STS-90 Mission Facts (Cont) Landed: Concrete runway 33 at Kennedy Space Center, Landed: Concrete runway 33 at Kennedy Space Center, Landed: Concrete runway 33 at Kennedy Space Center, Florida Florida Florida Payloads: Neurolab; Getaway Specials 197, 744 and 772; Payloads: Neurolab; Getaway Specials 197, 744 and 772; Payloads: Neurolab; Getaway Specials 197, 744 and 772; Shuttle Vibration Forces (SVFs); extended duration Shuttle Vibration Forces (SVFs); extended duration Shuttle Vibration Forces (SVFs); extended duration orbiter (EDO) cryogenic pallet; Bioreactor Demon- orbiter (EDO) cryogenic pallet; Bioreactor Demon- orbiter (EDO) cryogenic pallet; Bioreactor Demon- stration System (BDS) 04; DTOs and DSOs stration System (BDS) 04; DTOs and DSOs stration System (BDS) 04; DTOs and DSOs

STS-91 Mission Facts — Discovery— STS-91 Mission Facts — Discovery— STS-91 Mission Facts — Discovery— June 2–12, 1998 June 2–12, 1998 June 2–12, 1998

Commander: Charles (Charlie) J. Precourt Commander: Charles (Charlie) J. Precourt Commander: Charles (Charlie) J. Precourt Pilot: Dominic (Dom) L. Gorie Pilot: Dominic (Dom) L. Gorie Pilot: Dominic (Dom) L. Gorie Mission Specialist: Franklin Chang- Diaz Mission Specialist: Franklin Chang- Diaz Mission Specialist: Franklin Chang- Diaz Mission Specialist: Wendy Lawrence Mission Specialist: Wendy Lawrence Mission Specialist: Wendy Lawrence Mission Specialist: Janet Kavandi Mission Specialist: Janet Kavandi Mission Specialist: Janet Kavandi Mission Specialist: Valeriy Ryumin, Russian Space Mission Specialist: Valeriy Ryumin, Russian Space Mission Specialist: Valeriy Ryumin, Russian Space Agency Agency Agency Mission Specialist: Andrew (Andy) S.W. Thomas — Mission Specialist: Andrew (Andy) S.W. Thomas — Mission Specialist: Andrew (Andy) S.W. Thomas — down only down only down only Mission Duration: 216 hours (9 days), 19 hours, Mission Duration: 216 hours (9 days), 19 hours, Mission Duration: 216 hours (9 days), 19 hours, 55 minutes, 1 second 55 minutes, 1 second 55 minutes, 1 second Miles Traveled: Approximately 3.8 million statute miles Miles Traveled: Approximately 3.8 million statute miles Miles Traveled: Approximately 3.8 million statute miles Inclination: 51.6 degrees Inclination: 51.6 degrees Inclination: 51.6 degrees Orbits of Earth: 155 Orbits of Earth: 155 Orbits of Earth: 155 Orbital Altitude: 173 nautical miles (199 statute miles) at Orbital Altitude: 173 nautical miles (199 statute miles) at Orbital Altitude: 173 nautical miles (199 statute miles) at insertion; 213 nautical miles (245 statute miles) for insertion; 213 nautical miles (245 statute miles) for insertion; 213 nautical miles (245 statute miles) for Mir rendezvous Mir rendezvous Mir rendezvous Landing Touchdown: Approximately 1,309 feet beyond Landing Touchdown: Approximately 1,309 feet beyond Landing Touchdown: Approximately 1,309 feet beyond threshold threshold threshold Landing Rollout: Approximately 10,730 feet Landing Rollout: Approximately 10,730 feet Landing Rollout: Approximately 10,730 feet Orbiter Weight at Landing: Approximately 225,276 Orbiter Weight at Landing: Approximately 225,276 Orbiter Weight at Landing: Approximately 225,276 pounds pounds pounds Lift-off Weight: Approximately 4,514,510 pounds Lift-off Weight: Approximately 4,514,510 pounds Lift-off Weight: Approximately 4,514,510 pounds Orbiter Weight at Lift-off: Approximately 259,834 pounds Orbiter Weight at Lift-off: Approximately 259,834 pounds Orbiter Weight at Lift-off: Approximately 259,834 pounds Landing Speed at Main Gear Touchdown: Approximately Landing Speed at Main Gear Touchdown: Approximately Landing Speed at Main Gear Touchdown: Approximately 214 knots (246 miles per hour) 214 knots (246 miles per hour) 214 knots (246 miles per hour) Payload Weight Up: Approximately 25,922 pounds Payload Weight Up: Approximately 25,922 pounds Payload Weight Up: Approximately 25,922 pounds Payload Weight Down: Approximately 26,109 pounds Payload Weight Down: Approximately 26,109 pounds Payload Weight Down: Approximately 26,109 pounds Landed: Concrete runway 15 at Kennedy Space Center, Landed: Concrete runway 15 at Kennedy Space Center, Landed: Concrete runway 15 at Kennedy Space Center, Florida Florida Florida Payloads: SPACEHAB 09 single module/Mir 09; orbiter Payloads: SPACEHAB 09 single module/Mir 09; orbiter Payloads: SPACEHAB 09 single module/Mir 09; orbiter docking system; getaway specials (8): G-090, G- docking system; getaway specials (8): G-090, G- docking system; getaway specials (8): G-090, G- 743, G-765, G-648, two Space Experiment Mod- 743, G-765, G-648, two Space Experiment Mod- 743, G-765, G-648, two Space Experiment Mod- ules (SEMs) (SEM 03 and SEM 05), two Phase 1 ules (SEMs) (SEM 03 and SEM 05), two Phase 1 ules (SEMs) (SEM 03 and SEM 05), two Phase 1 Program Support Packages (PH1 PSP1 and PH1 Program Support Packages (PH1 PSP1 and PH1 Program Support Packages (PH1 PSP1 and PH1 PSP2); Alpha Magnetic Spectrometer (AMS); Phase PSP2); Alpha Magnetic Spectrometer (AMS); Phase PSP2); Alpha Magnetic Spectrometer (AMS); Phase 1 requirements (Shuttle/Mir Mission 09 middeck sci- 1 requirements (Shuttle/Mir Mission 09 middeck sci- 1 requirements (Shuttle/Mir Mission 09 middeck sci- ence, mission support equipment and risk mitigation ence, mission support equipment and risk mitigation ence, mission support equipment and risk mitigation experiments); Commercial Protein Crystal Growth experiments); Commercial Protein Crystal Growth experiments); Commercial Protein Crystal Growth (CPCG); Solid Surface Combustion Experiment (CPCG); Solid Surface Combustion Experiment (CPCG); Solid Surface Combustion Experiment (SSCE); Shuttle Ionospheric Modification with Pulsed (SSCE); Shuttle Ionospheric Modification with Pulsed (SSCE); Shuttle Ionospheric Modification with Pulsed Local Exhaust (SIMPLEX, payload of opportunity; Local Exhaust (SIMPLEX, payload of opportunity; Local Exhaust (SIMPLEX, payload of opportunity; DTOs, DSO, RMEs and HTD DTOs, DSO, RMEs and HTD DTOs, DSO, RMEs and HTD

Y-75 Y-75 Y-75 STS-95 Mission Facts — Discovery— STS-95 Mission Facts — Discovery— STS-95 Mission Facts — Discovery— October 29–November 7, 1998 October 29–November 7, 1998 October 29–November 7, 1998 Commander: Curtis L. Brown, Jr. Commander: Curtis L. Brown, Jr. Commander: Curtis L. Brown, Jr. Pilot: Steven W. Lindsey Pilot: Steven W. Lindsey Pilot: Steven W. Lindsey Mission Specialist: Scott E. Parazynski Mission Specialist: Scott E. Parazynski Mission Specialist: Scott E. Parazynski Mission Specialist: Stephen K. Robinson Mission Specialist: Stephen K. Robinson Mission Specialist: Stephen K. Robinson Mission Specialist: Pedro Duque, European Space Mission Specialist: Pedro Duque, European Space Mission Specialist: Pedro Duque, European Space Agency Agency Agency Payload Specialist: Chiaki Mukai, National Space Payload Specialist: Chiaki Mukai, National Space Payload Specialist: Chiaki Mukai, National Space Development Agency of Japan Development Agency of Japan Development Agency of Japan Payload Specialist: Senator John Glenn Payload Specialist: Senator John Glenn Payload Specialist: Senator John Glenn Mission Duration: 192 hours (8 days), 21 hours, Mission Duration: 192 hours (8 days), 21 hours, Mission Duration: 192 hours (8 days), 21 hours, 44 minutes, 56 seconds 44 minutes, 56 seconds 44 minutes, 56 seconds Miles Traveled: Approximately 3.6 million statute miles Miles Traveled: Approximately 3.6 million statute miles Miles Traveled: Approximately 3.6 million statute miles Inclination: 28.45 degrees Inclination: 28.45 degrees Inclination: 28.45 degrees Orbits of Earth: 135 Orbits of Earth: 135 Orbits of Earth: 135 Orbital Altitude: 300 nautical miles (345 statute miles) Orbital Altitude: 300 nautical miles (345 statute miles) Orbital Altitude: 300 nautical miles (345 statute miles) Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately 227,783 pounds 227,783 pounds 227,783 pounds Lift-off Weight: Approximately 4,521,918 pounds Lift-off Weight: Approximately 4,521,918 pounds Lift-off Weight: Approximately 4,521,918 pounds Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately 227,207 pounds 227,207 pounds 227,207 pounds Payload Weight Up: Approximately 28,520 pounds Payload Weight Up: Approximately 28,520 pounds Payload Weight Up: Approximately 28,520 pounds Payload Weight Down: Approximately 28,367 pounds Payload Weight Down: Approximately 28,367 pounds Payload Weight Down: Approximately 28,367 pounds Landing Touchdown: Approximately 3,333 feet beyond Landing Touchdown: Approximately 3,333 feet beyond Landing Touchdown: Approximately 3,333 feet beyond threshold threshold threshold Landing Rollout: Approximately 9,511 feet Landing Rollout: Approximately 9,511 feet Landing Rollout: Approximately 9,511 feet Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 199 knots (229 miles per hour) mately 199 knots (229 miles per hour) mately 199 knots (229 miles per hour) Landed: Kennedy Space Center, Florida Landed: Kennedy Space Center, Florida Landed: Kennedy Space Center, Florida Payloads: SPACEHAB; SPARTAN 201-5; Hubble Space Payloads: SPACEHAB; SPARTAN 201-5; Hubble Space Payloads: SPACEHAB; SPARTAN 201-5; Hubble Space Telescope Orbital Systems Test Platform (HOST); Telescope Orbital Systems Test Platform (HOST); Telescope Orbital Systems Test Platform (HOST); International Extreme Ultraviolet Hitchhiker (IEH)- International Extreme Ultraviolet Hitchhiker (IEH)- International Extreme Ultraviolet Hitchhiker (IEH)- 3; Cryogenic Thermal Storage Unit (CRYOTSU); 3; Cryogenic Thermal Storage Unit (CRYOTSU); 3; Cryogenic Thermal Storage Unit (CRYOTSU); Space Experiment Module (SEM)-4; Getaway Space Experiment Module (SEM)-4; Getaway Space Experiment Module (SEM)-4; Getaway Special (GAS) program; Biological Research in Special (GAS) program; Biological Research in Special (GAS) program; Biological Research in Canisters (BRIC); Electronic Nose Canisters (BRIC); Electronic Nose Canisters (BRIC); Electronic Nose (E-NOSE) (E-NOSE) (E-NOSE)

STS-88 Mission Facts — Endeavour— STS-88 Mission Facts — Endeavour— STS-88 Mission Facts — Endeavour— December 4–15, 1998 December 4–15, 1998 December 4–15, 1998

Commander: Robert D. Cabana Commander: Robert D. Cabana Commander: Robert D. Cabana Pilot: Frederick W. “Rick” Sturckow Pilot: Frederick W. “Rick” Sturckow Pilot: Frederick W. “Rick” Sturckow Mission Specialist: Nancy J. Currie Mission Specialist: Nancy J. Currie Mission Specialist: Nancy J. Currie Mission Specialist: Jerry L. Ross Mission Specialist: Jerry L. Ross Mission Specialist: Jerry L. Ross Mission Specialist: James H. Newman Mission Specialist: James H. Newman Mission Specialist: James H. Newman Mission Specialist: Sergei Konstantinovich Krikalev, Mission Specialist: Sergei Konstantinovich Krikalev, Mission Specialist: Sergei Konstantinovich Krikalev, Russian Space Agency Russian Space Agency Russian Space Agency Mission Duration: 264 hours (11 days), 19 hours, Mission Duration: 264 hours (11 days), 19 hours, Mission Duration: 264 hours (11 days), 19 hours, 18 minutes, 47 seconds 18 minutes, 47 seconds 18 minutes, 47 seconds

Y-76 Y-76 Y-76 STS-88 Mission Facts (Cont) STS-88 Mission Facts (Cont) STS-88 Mission Facts (Cont) Miles Traveled: Approximately 4.6 million statute miles Miles Traveled: Approximately 4.6 million statute miles Miles Traveled: Approximately 4.6 million statute miles Inclination: 51.6 degrees Inclination: 51.6 degrees Inclination: 51.6 degrees Orbits of Earth: 186 Orbits of Earth: 186 Orbits of Earth: 186 Orbital Altitude: 173 nautical miles (199 statute miles) Orbital Altitude: 173 nautical miles (199 statute miles) Orbital Altitude: 173 nautical miles (199 statute miles) Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately 200,296 pounds 200,296 pounds 200,296 pounds Lift-off Weight: Approximately 4,518,390 pounds Lift-off Weight: Approximately 4,518,390 pounds Lift-off Weight: Approximately 4,518,390 pounds Orbiter Weight at Lift-off: Approximately 263,927 pounds Orbiter Weight at Lift-off: Approximately 263,927 pounds Orbiter Weight at Lift-off: Approximately 263,927 pounds Payload Weight Up: Approximately 30,986 pounds Payload Weight Up: Approximately 30,986 pounds Payload Weight Up: Approximately 30,986 pounds Payload Weight Down: Approximately 4,500 pounds Payload Weight Down: Approximately 4,500 pounds Payload Weight Down: Approximately 4,500 pounds Landing Touchdown: Approximately 3,291 feet beyond Landing Touchdown: Approximately 3,291 feet beyond Landing Touchdown: Approximately 3,291 feet beyond threshold threshold threshold Landing Rollout: Approximately 8,322 feet Landing Rollout: Approximately 8,322 feet Landing Rollout: Approximately 8,322 feet Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 197 knots (227 miles per hour) mately 197 knots (227 miles per hour) mately 197 knots (227 miles per hour) Landed: Concrete runway 15 at Kennedy Space Center, Landed: Concrete runway 15 at Kennedy Space Center, Landed: Concrete runway 15 at Kennedy Space Center, Florida Florida Florida Payloads: ISS Unity connecting module; IMAX cargo bay Payloads: ISS Unity connecting module; IMAX cargo bay Payloads: ISS Unity connecting module; IMAX cargo bay camera (ICBC); Satelite de Aplicaciones/ Cientifico camera (ICBC); Satelite de Aplicaciones/ Cientifico camera (ICBC); Satelite de Aplicaciones/ Cientifico A (SAC-A); MightySat 1; Space Experiment Module A (SAC-A); MightySat 1; Space Experiment Module A (SAC-A); MightySat 1; Space Experiment Module (SEM) 07; getaway special (G-093) (SEM) 07; getaway special (G-093) (SEM) 07; getaway special (G-093) Extravehicular Activity (EVA): EVA 1, Jerry Ross and Extravehicular Activity (EVA): EVA 1, Jerry Ross and Extravehicular Activity (EVA): EVA 1, Jerry Ross and Jim Newman, 7 hours, 21 minutes; EVA 2, Jerry Jim Newman, 7 hours, 21 minutes; EVA 2, Jerry Jim Newman, 7 hours, 21 minutes; EVA 2, Jerry Ross and Jim Newman, 7 hours, 2 minutes; EVA 3, Ross and Jim Newman, 7 hours, 2 minutes; EVA 3, Ross and Jim Newman, 7 hours, 2 minutes; EVA 3, Jerry Ross and Jim Newman, 6 hours, 59 minutes. Jerry Ross and Jim Newman, 6 hours, 59 minutes. Jerry Ross and Jim Newman, 6 hours, 59 minutes. During EVA 1, Ross and Newman made all umbili- During EVA 1, Ross and Newman made all umbili- During EVA 1, Ross and Newman made all umbili- cal connections necessary to activate Node 1. cal connections necessary to activate Node 1. cal connections necessary to activate Node 1. Upon completion, the ground sent commands to Upon completion, the ground sent commands to Upon completion, the ground sent commands to the node to confirm power and activation. During the node to confirm power and activation. During the node to confirm power and activation. During EVA 2, Ross and Newman installed EVA transla- EVA 2, Ross and Newman installed EVA transla- EVA 2, Ross and Newman installed EVA transla- tion aids and tools and early communications tion aids and tools and early communications tion aids and tools and early communications system antennas and routed the comm cable from system antennas and routed the comm cable from system antennas and routed the comm cable from the FGB to the starboard antenna. EVA 3 was the FGB to the starboard antenna. EVA 3 was the FGB to the starboard antenna. EVA 3 was performed to support objectives of downstream performed to support objectives of downstream performed to support objectives of downstream assembly missions. Tasks included installation of assembly missions. Tasks included installation of assembly missions. Tasks included installation of a large tool bag for storing EVA tools outside the a large tool bag for storing EVA tools outside the a large tool bag for storing EVA tools outside the station and repositioning foot restraints. Addition- station and repositioning foot restraints. Addition- station and repositioning foot restraints. Addition- ally, Ross and Newman disconnected the umbili- ally, Ross and Newman disconnected the umbili- ally, Ross and Newman disconnected the umbili- cal on PMA-2 so that PMA-2 can be relocated in cal on PMA-2 so that PMA-2 can be relocated in cal on PMA-2 so that PMA-2 can be relocated in the future. the future. the future.

Y-77 Y-77 Y-77 STS-96 Mission Facts — Discovery — STS-96 Mission Facts — Discovery — STS-96 Mission Facts — Discovery — May 27–June 6, 1999 May 27–June 6, 1999 May 27–June 6, 1999 Commander: Kent V. Rominger Commander: Kent V. Rominger Commander: Kent V. Rominger Pilot: Rick D. Husband Pilot: Rick D. Husband Pilot: Rick D. Husband Mission Specialist: Ellen Ochoa Mission Specialist: Ellen Ochoa Mission Specialist: Ellen Ochoa Mission Specialist: Tamara E. Jernigan Mission Specialist: Tamara E. Jernigan Mission Specialist: Tamara E. Jernigan Mission Specialist: Daniel T. Barry Mission Specialist: Daniel T. Barry Mission Specialist: Daniel T. Barry Mission Specialist: Julie Payette, Canadian Space Mission Specialist: Julie Payette, Canadian Space Mission Specialist: Julie Payette, Canadian Space Agency Agency Agency Mission Specialist: Valery Ivanovich Tokarev, Russian Mission Specialist: Valery Ivanovich Tokarev, Russian Mission Specialist: Valery Ivanovich Tokarev, Russian Space Agency Space Agency Space Agency Mission Duration: 216 hours (9 days), 19 hours, Mission Duration: 216 hours (9 days), 19 hours, Mission Duration: 216 hours (9 days), 19 hours, 13 minutes, 57 seconds 13 minutes, 57 seconds 13 minutes, 57 seconds Miles Traveled: Approximately 4,051,000 statute miles Miles Traveled: Approximately 4,051,000 statute miles Miles Traveled: Approximately 4,051,000 statute miles Inclination: 51.6 degrees Inclination: 51.6 degrees Inclination: 51.6 degrees Orbits of Earth: 154 Orbits of Earth: 154 Orbits of Earth: 154 Orbital Altitude: 173 nautical miles (199 statute miles) Orbital Altitude: 173 nautical miles (199 statute miles) Orbital Altitude: 173 nautical miles (199 statute miles) Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately 221,664 pounds 221,664 pounds 221,664 pounds Lift-off Weight: Approximately 4,514,231 pounds Lift-off Weight: Approximately 4,514,231 pounds Lift-off Weight: Approximately 4,514,231 pounds Orbiter Weight at Lift-off: Approximately 227,974 pounds Orbiter Weight at Lift-off: Approximately 227,974 pounds Orbiter Weight at Lift-off: Approximately 227,974 pounds Payload Weight Up: Approximately 22,707 pounds Payload Weight Up: Approximately 22,707 pounds Payload Weight Up: Approximately 22,707 pounds Payload Weight Down: Approximately 19,390 pounds Payload Weight Down: Approximately 19,390 pounds Payload Weight Down: Approximately 19,390 pounds Landing Touchdown: Approximately 2,084 feet beyond Landing Touchdown: Approximately 2,084 feet beyond Landing Touchdown: Approximately 2,084 feet beyond threshold threshold threshold Landing Rollout: Approximately 8,848 feet Landing Rollout: Approximately 8,848 feet Landing Rollout: Approximately 8,848 feet Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 211 knots (243 miles per hour) mately 211 knots (243 miles per hour) mately 211 knots (243 miles per hour) Landed: Concrete runway 15 at Kennedy Space Center, Landed: Concrete runway 15 at Kennedy Space Center, Landed: Concrete runway 15 at Kennedy Space Center, Florida Florida Florida Payloads: International Space Station (A.1); SPACEHAB Payloads: International Space Station (A.1); SPACEHAB Payloads: International Space Station (A.1); SPACEHAB double module; Integrated Vehicle Health Monitor- double module; Integrated Vehicle Health Monitor- double module; Integrated Vehicle Health Monitor- ing HEDS Technology Demonstration 2; Student- ing HEDS Technology Demonstration 2; Student- ing HEDS Technology Demonstration 2; Student- Tracked Atmospheric Research Satellite for Heuristic Tracked Atmospheric Research Satellite for Heuristic Tracked Atmospheric Research Satellite for Heuristic International Networking Equipment (STARSHINE); International Networking Equipment (STARSHINE); International Networking Equipment (STARSHINE); Shuttle Vibration Forces Experiment; MIRTS change- Shuttle Vibration Forces Experiment; MIRTS change- Shuttle Vibration Forces Experiment; MIRTS change- out; cargo transfer out; cargo transfer out; cargo transfer Extravehicular Activity (EVA): EVA 1, Tammy Jernigan Extravehicular Activity (EVA): EVA 1, Tammy Jernigan Extravehicular Activity (EVA): EVA 1, Tammy Jernigan and Dan Barry, 7 hours, 55 minutes. During the and Dan Barry, 7 hours, 55 minutes. During the and Dan Barry, 7 hours, 55 minutes. During the EVA, Jernigan and Barry transferred and installed EVA, Jernigan and Barry transferred and installed EVA, Jernigan and Barry transferred and installed two cranes from the Shuttle’s payload bay to two cranes from the Shuttle’s payload bay to two cranes from the Shuttle’s payload bay to locations on the outside of the station. They also locations on the outside of the station. They also locations on the outside of the station. They also installed two new portable foot restraints that will installed two new portable foot restraints that will installed two new portable foot restraints that will fit both American and Russian space boots, and fit both American and Russian space boots, and fit both American and Russian space boots, and attached three bags filled with tools and handrails attached three bags filled with tools and handrails attached three bags filled with tools and handrails that will be used during future assembly opera- that will be used during future assembly opera- that will be used during future assembly opera- tions. Once those primary tasks were accom- tions. Once those primary tasks were accom- tions. Once those primary tasks were accom- plished, Jernigan and Barry installed an insulating plished, Jernigan and Barry installed an insulating plished, Jernigan and Barry installed an insulating cover on a trunnion pin on the Unity module, cover on a trunnion pin on the Unity module, cover on a trunnion pin on the Unity module,

Y-78 Y-78 Y-78 STS-96 Mission Facts — (Cont) STS-96 Mission Facts — (Cont) STS-96 Mission Facts — (Cont) documented painted surfaces on both the Unity documented painted surfaces on both the Unity documented painted surfaces on both the Unity and Zarya modules, and inspected one of two and Zarya modules, and inspected one of two and Zarya modules, and inspected one of two early communications system antennas on the early communications system antennas on the early communications system antennas on the Unity. Other tasks completed during the space- Unity. Other tasks completed during the space- Unity. Other tasks completed during the space- walk included moving foot restraints into PMA-1 walk included moving foot restraints into PMA-1 walk included moving foot restraints into PMA-1 (Primary Mating Adapter) and installing three (Primary Mating Adapter) and installing three (Primary Mating Adapter) and installing three bags containing tools for use during later flights. bags containing tools for use during later flights. bags containing tools for use during later flights. Throughout the spacewalk, Jernigan and Barry Throughout the spacewalk, Jernigan and Barry Throughout the spacewalk, Jernigan and Barry were assisted by their crew mates as Mission were assisted by their crew mates as Mission were assisted by their crew mates as Mission Specialist Ellen Ochoa operated the Shuttle’s robot Specialist Ellen Ochoa operated the Shuttle’s robot Specialist Ellen Ochoa operated the Shuttle’s robot arm to maneuver Jernigan around Discovery’s arm to maneuver Jernigan around Discovery’s arm to maneuver Jernigan around Discovery’s cargo bay, and Canadian Space Agency astronaut cargo bay, and Canadian Space Agency astronaut cargo bay, and Canadian Space Agency astronaut Julie Payette acted as “choreographer” of the Julie Payette acted as “choreographer” of the Julie Payette acted as “choreographer” of the spacewalk from Discovery’s flight deck. spacewalk from Discovery’s flight deck. spacewalk from Discovery’s flight deck.

STS-93 Mission Facts — Columbia — STS-93 Mission Facts — Columbia — STS-93 Mission Facts — Columbia — July 23–27, 1999 July 23–27, 1999 July 23–27, 1999

Commander: Eileen M. Collins Commander: Eileen M. Collins Commander: Eileen M. Collins Pilot: Jeffrey S. Ashby Pilot: Jeffrey S. Ashby Pilot: Jeffrey S. Ashby Mission Specialist: Steven A. Hawley Mission Specialist: Steven A. Hawley Mission Specialist: Steven A. Hawley Mission Specialist: Catherine G. Coleman Mission Specialist: Catherine G. Coleman Mission Specialist: Catherine G. Coleman Mission Specialist: Michael Tognini, CNES Mission Specialist: Michael Tognini, CNES Mission Specialist: Michael Tognini, CNES Mission Duration: 96 hours (4 days), 22 hours, Mission Duration: 96 hours (4 days), 22 hours, Mission Duration: 96 hours (4 days), 22 hours, 50 minutes, 22 seconds 50 minutes, 22 seconds 50 minutes, 22 seconds Miles Traveled: Approximately 1.8 million statute miles Miles Traveled: Approximately 1.8 million statute miles Miles Traveled: Approximately 1.8 million statute miles Inclination: 28.45 degrees Inclination: 28.45 degrees Inclination: 28.45 degrees Orbits of Earth: 80 Orbits of Earth: 80 Orbits of Earth: 80 Orbital Altitude: 153 nautical miles (176 statute miles) Orbital Altitude: 153 nautical miles (176 statute miles) Orbital Altitude: 153 nautical miles (176 statute miles) Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately Orbiter Weight at Landing: Approximately 202,338 pounds 202,338 pounds 202,338 pounds Lift-off Weight: Approximately 4,524,972 pounds Lift-off Weight: Approximately 4,524,972 pounds Lift-off Weight: Approximately 4,524,972 pounds Orbiter Weight at Lift-off: Approximately 270,387 pounds Orbiter Weight at Lift-off: Approximately 270,387 pounds Orbiter Weight at Lift-off: Approximately 270,387 pounds Payload Weight Up: Approximately 49,789 pounds Payload Weight Up: Approximately 49,789 pounds Payload Weight Up: Approximately 49,789 pounds Payload Weight Down: Approximately 6,709 pounds Payload Weight Down: Approximately 6,709 pounds Payload Weight Down: Approximately 6,709 pounds Landing Touchdown: Approximately 2,696 feet beyond Landing Touchdown: Approximately 2,696 feet beyond Landing Touchdown: Approximately 2,696 feet beyond threshold threshold threshold Landing Rollout: Approximately 6,777 feet Landing Rollout: Approximately 6,777 feet Landing Rollout: Approximately 6,777 feet Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 201 knots (231 miles per hour) mately 201 knots (231 miles per hour) mately 201 knots (231 miles per hour) Landed: Concrete runway 33 at Kennedy Space Center, Landed: Concrete runway 33 at Kennedy Space Center, Landed: Concrete runway 33 at Kennedy Space Center, Florida Florida Florida Payloads: Chandra X-Ray Observatory (CXO); Plant Payloads: Chandra X-Ray Observatory (CXO); Plant Payloads: Chandra X-Ray Observatory (CXO); Plant Growth Investigations in Microgravity 1; Southwest Growth Investigations in Microgravity 1; Southwest Growth Investigations in Microgravity 1; Southwest Ultraviolet Imaging System; Gelation of Sols: Ultraviolet Imaging System; Gelation of Sols: Ultraviolet Imaging System; Gelation of Sols: Applied Microgravity Research; Space Tissue Loss; Applied Microgravity Research; Space Tissue Loss; Applied Microgravity Research; Space Tissue Loss; Lightweight Flexible Solar Array Hinge; Cell Lightweight Flexible Solar Array Hinge; Cell Lightweight Flexible Solar Array Hinge; Cell

Y-79 Y-79 Y-79 STS-93 Mission Facts (Cont) STS-93 Mission Facts (Cont) STS-93 Mission Facts (Cont) Culture Module, Configuration C; Shuttle Amateur Culture Module, Configuration C; Shuttle Amateur Culture Module, Configuration C; Shuttle Amateur Radio Experiment II; Commercial Generic Bio- Radio Experiment II; Commercial Generic Bio- Radio Experiment II; Commercial Generic Bio- processing Apparatus; Micro-Electro-Mechanical processing Apparatus; Micro-Electro-Mechanical processing Apparatus; Micro-Electro-Mechanical Systems; Biological Research in Canisters Systems; Biological Research in Canisters Systems; Biological Research in Canisters

STS-103 Mission Facts — Discovery — STS-103 Mission Facts — Discovery — STS-103 Mission Facts — Discovery — Dec. 19–27, 1999 Dec. 19–27, 1999 Dec. 19–27, 1999

Commander: Curtis L. Brown Commander: Curtis L. Brown Commander: Curtis L. Brown Pilot: Scott J. Kelly Pilot: Scott J. Kelly Pilot: Scott J. Kelly Mission Specialist: Jean-Francois Clervoy, European Mission Specialist: Jean-Francois Clervoy, European Mission Specialist: Jean-Francois Clervoy, European Space Agency Space Agency Space Agency Mission Specialist: Steven L. Smith Mission Specialist: Steven L. Smith Mission Specialist: Steven L. Smith Mission Specialist: C. Michael Foale Mission Specialist: C. Michael Foale Mission Specialist: C. Michael Foale Mission Specialist: John M. Grunsfeld Mission Specialist: John M. Grunsfeld Mission Specialist: John M. Grunsfeld Mission Specialist: Claude Nicollier, European Space Mission Specialist: Claude Nicollier, European Space Mission Specialist: Claude Nicollier, European Space Agency Agency Agency Mission Duration: 168 hours (7 days), 23 hours, Mission Duration: 168 hours (7 days), 23 hours, Mission Duration: 168 hours (7 days), 23 hours, 10 minutes, 47 seconds 10 minutes, 47 seconds 10 minutes, 47 seconds Miles Traveled: Approximately 3,267,000 statute miles Miles Traveled: Approximately 3,267,000 statute miles Miles Traveled: Approximately 3,267,000 statute miles Inclination: 28.45 degrees Inclination: 28.45 degrees Inclination: 28.45 degrees Orbits of Earth: 120 Orbits of Earth: 120 Orbits of Earth: 120 Orbital Altitude: 317 nautical miles (365 statute miles) Orbital Altitude: 317 nautical miles (365 statute miles) Orbital Altitude: 317 nautical miles (365 statute miles) Orbiter Weight at Landing: 210,977 Orbiter Weight at Landing: 210,977 Orbiter Weight at Landing: 210,977 Lift-off Weight: Approximately 4,506,419 pounds Lift-off Weight: Approximately 4,506,419 pounds Lift-off Weight: Approximately 4,506,419 pounds Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately 248,159 pounds 248,159 pounds 248,159 pounds Payload Weight Up: Approximately 13,208 pounds Payload Weight Up: Approximately 13,208 pounds Payload Weight Up: Approximately 13,208 pounds Payload Weight Down: Approximately 13,136 pounds Payload Weight Down: Approximately 13,136 pounds Payload Weight Down: Approximately 13,136 pounds Landing Touchdown: Approximately 2,926 feet beyond Landing Touchdown: Approximately 2,926 feet beyond Landing Touchdown: Approximately 2,926 feet beyond threshold threshold threshold Landing Rollout: Approximately 6,975 feet Landing Rollout: Approximately 6,975 feet Landing Rollout: Approximately 6,975 feet Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- Landing Speed at Main Gear Touchdown: Approxi- mately 187 knots (215 miles per hour) mately 187 knots (215 miles per hour) mately 187 knots (215 miles per hour) Landed: Concrete runway 33 at Kennedy Space Center, Landed: Concrete runway 33 at Kennedy Space Center, Landed: Concrete runway 33 at Kennedy Space Center, Florida Florida Florida Payload: Hubble Space Telescope servicing mission Payload: Hubble Space Telescope servicing mission Payload: Hubble Space Telescope servicing mission 03-A (fine guidance sensor; gyroscopes; new 03-A (fine guidance sensor; gyroscopes; new 03-A (fine guidance sensor; gyroscopes; new advanced computer; new thermal blanket layers; advanced computer; new thermal blanket layers; advanced computer; new thermal blanket layers; S-band single-access transmitter; solid-state S-band single-access transmitter; solid-state S-band single-access transmitter; solid-state recorder; and voltage/temperature improvement recorder; and voltage/temperature improvement recorder; and voltage/temperature improvement kits) kits) kits)

Y-80 Y-80 Y-80 STS-103 Mission Facts (Cont) STS-103 Mission Facts (Cont) STS-103 Mission Facts (Cont)

Extravehicular Activity (EVA): EVA 1, Steve Smith and Extravehicular Activity (EVA): EVA 1, Steve Smith and Extravehicular Activity (EVA): EVA 1, Steve Smith and John Grunsfeld, 8 hours, 15 minutes. During John Grunsfeld, 8 hours, 15 minutes. During John Grunsfeld, 8 hours, 15 minutes. During the EVA, Smith and Grunsfeld installed six new the EVA, Smith and Grunsfeld installed six new the EVA, Smith and Grunsfeld installed six new gyroscopes and six voltage/temperature improve- gyroscopes and six voltage/temperature improve- gyroscopes and six voltage/temperature improve- ment kits in the telescope. EVA 2, Mike Foale and ment kits in the telescope. EVA 2, Mike Foale and ment kits in the telescope. EVA 2, Mike Foale and Claude Nicollier, 8 hours, 10 minutes. During the Claude Nicollier, 8 hours, 10 minutes. During the Claude Nicollier, 8 hours, 10 minutes. During the EVA, they installed a new advanced computer, EVA, they installed a new advanced computer, EVA, they installed a new advanced computer, 20 times faster and with six times the memory of 20 times faster and with six times the memory of 20 times faster and with six times the memory of the previous machine, and replaced a 550-lb. fine the previous machine, and replaced a 550-lb. fine the previous machine, and replaced a 550-lb. fine guidance sensor, one of three on the telescope. guidance sensor, one of three on the telescope. guidance sensor, one of three on the telescope. EVA 3, Smith and Grunsfeld, 8 hours, 8 minutes. EVA 3, Smith and Grunsfeld, 8 hours, 8 minutes. EVA 3, Smith and Grunsfeld, 8 hours, 8 minutes. During the EVA, Smith and Grunsfeld replaced a During the EVA, Smith and Grunsfeld replaced a During the EVA, Smith and Grunsfeld replaced a failed radio transmitter and installed a new digital failed radio transmitter and installed a new digital failed radio transmitter and installed a new digital solid-state recorder that will provide more than 10 solid-state recorder that will provide more than 10 solid-state recorder that will provide more than 10 times the storage capacity of the old unit. They also times the storage capacity of the old unit. They also times the storage capacity of the old unit. They also applied new insulation on two equipment bay doors. applied new insulation on two equipment bay doors. applied new insulation on two equipment bay doors. Both the transmitter and the recorder checked out Both the transmitter and the recorder checked out Both the transmitter and the recorder checked out normally on early tests by telescope controllers. Total normally on early tests by telescope controllers. Total normally on early tests by telescope controllers. Total time servicing the Hubble: 93 hours, 13 minutes. time servicing the Hubble: 93 hours, 13 minutes. time servicing the Hubble: 93 hours, 13 minutes.

STS-99 Mission Facts — Endeavour — STS-99 Mission Facts — Endeavour — STS-99 Mission Facts — Endeavour — Feb. 11–22, 2000 Feb. 11–22, 2000 Feb. 11–22, 2000

Commander: Kevin R. Kregel Commander: Kevin R. Kregel Commander: Kevin R. Kregel Pilot: Dom L. Gorie Pilot: Dom L. Gorie Pilot: Dom L. Gorie Mission Specialist: Gerhard P.J. Thiele Mission Specialist: Gerhard P.J. Thiele Mission Specialist: Gerhard P.J. Thiele Mission Specialist: Janet L. Kavandi Mission Specialist: Janet L. Kavandi Mission Specialist: Janet L. Kavandi Mission Specialist: Janice Voss Mission Specialist: Janice Voss Mission Specialist: Janice Voss Mission Specialist: Mamoru Mohri Mission Specialist: Mamoru Mohri Mission Specialist: Mamoru Mohri Mission Duration: 264 hours (11 days), 5 hours, Mission Duration: 264 hours (11 days), 5 hours, Mission Duration: 264 hours (11 days), 5 hours, 38 minutes 38 minutes 38 minutes Miles Traveled: Approximately 4 million statute miles Miles Traveled: Approximately 4 million statute miles Miles Traveled: Approximately 4 million statute miles Inclination: 57 degrees Inclination: 57 degrees Inclination: 57 degrees Orbits of Earth: 182 Orbits of Earth: 182 Orbits of Earth: 182 Orbital Altitude: 126 nautical miles (approximately Orbital Altitude: 126 nautical miles (approximately Orbital Altitude: 126 nautical miles (approximately 145 statute miles) 145 statute miles) 145 statute miles) Orbiter Weight at Landing: 225,669 pounds Orbiter Weight at Landing: 225,669 pounds Orbiter Weight at Landing: 225,669 pounds Lift-off Weight: Approximately 4,520,415 pounds Lift-off Weight: Approximately 4,520,415 pounds Lift-off Weight: Approximately 4,520,415 pounds Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately Orbiter Weight at Lift-off: Approximately 256,560 pounds 256,560 pounds 256,560 pounds Payload Weight Up: Approximately 14.5 tons Payload Weight Up: Approximately 14.5 tons Payload Weight Up: Approximately 14.5 tons (29,000 pounds) (29,000 pounds) (29,000 pounds) Payload Weight Down: Approximately 28,740 pounds Payload Weight Down: Approximately 28,740 pounds Payload Weight Down: Approximately 28,740 pounds Landing Touchdown: Approximately 2,967 feet beyond Landing Touchdown: Approximately 2,967 feet beyond Landing Touchdown: Approximately 2,967 feet beyond threshold threshold threshold Landing Rollout: Approximately 9,954 feet Landing Rollout: Approximately 9,954 feet Landing Rollout: Approximately 9,954 feet Landing Speed at Main Gear Touchdown: Approximately Landing Speed at Main Gear Touchdown: Approximately Landing Speed at Main Gear Touchdown: Approximately 206 knots (237 miles per hour) 206 knots (237 miles per hour) 206 knots (237 miles per hour) Landed: Concrete runway 33 at Kennedy Space Center, Landed: Concrete runway 33 at Kennedy Space Center, Landed: Concrete runway 33 at Kennedy Space Center, Fla. Fla. Fla.

Y-81 Y-81 Y-81 STS-99 Mission Facts (Cont) STS-99 Mission Facts (Cont) STS-99 Mission Facts (Cont)

Payload: Shuttle Radar Topography Mission hardware Payload: Shuttle Radar Topography Mission hardware Payload: Shuttle Radar Topography Mission hardware (mast, antenna, and data recording, processing (mast, antenna, and data recording, processing (mast, antenna, and data recording, processing products) products) products)

STS-101/2A.2a Mission Facts — Atlantis — STS-101/2A.2a Mission Facts — Atlantis — STS-101/2A.2a Mission Facts — Atlantis — May 19–29, 2000 May 19–29, 2000 May 19–29, 2000

Commander: James D. Halsell Commander: James D. Halsell Commander: James D. Halsell Pilot: Scott J. Horowitz Pilot: Scott J. Horowitz Pilot: Scott J. Horowitz Mission Specialist: Mary Ellen Weber Mission Specialist: Mary Ellen Weber Mission Specialist: Mary Ellen Weber Mission Specialist: Jeffrey N. Williams Mission Specialist: Jeffrey N. Williams Mission Specialist: Jeffrey N. Williams Mission Specialist: James S. Voss Mission Specialist: James S. Voss Mission Specialist: James S. Voss Mission Specialist: Susan J. Helms Mission Specialist: Susan J. Helms Mission Specialist: Susan J. Helms Mission Specialist: Yuri V. Usachev Mission Specialist: Yuri V. Usachev Mission Specialist: Yuri V. Usachev Mission Duration: 216 hours (9 days), 20 hours, Mission Duration: 216 hours (9 days), 20 hours, Mission Duration: 216 hours (9 days), 20 hours, 10 minutes 10 minutes 10 minutes Miles Traveled: 4,076,241 statute miles Miles Traveled: 4,076,241 statute miles Miles Traveled: 4,076,241 statute miles Inclination: 51.6 degrees Inclination: 51.6 degrees Inclination: 51.6 degrees Orbits of Earth: 156 Orbits of Earth: 156 Orbits of Earth: 156 Orbital Altitude: 173 nautical miles (approximately Orbital Altitude: 173 nautical miles (approximately Orbital Altitude: 173 nautical miles (approximately 259 statute miles) 259 statute miles) 259 statute miles) Orbiter Weight at Landing: 221,271 pounds Orbiter Weight at Landing: 221,271 pounds Orbiter Weight at Landing: 221,271 pounds Lift-off Weight: 4,519,645 pounds Lift-off Weight: 4,519,645 pounds Lift-off Weight: 4,519,645 pounds Orbiter Weight at Lift-off: 262,528 pounds Orbiter Weight at Lift-off: 262,528 pounds Orbiter Weight at Lift-off: 262,528 pounds Payload Weight Up: 24,733 pounds Payload Weight Up: 24,733 pounds Payload Weight Up: 24,733 pounds Payload Weight Down: 23,074 pounds Payload Weight Down: 23,074 pounds Payload Weight Down: 23,074 pounds Landing Touchdown: Approximately 3,359 feet beyond Landing Touchdown: Approximately 3,359 feet beyond Landing Touchdown: Approximately 3,359 feet beyond threshold threshold threshold Landing Rollout: Approximately 8,917 feet Landing Rollout: Approximately 8,917 feet Landing Rollout: Approximately 8,917 feet Landing Speed at Main Gear Touchdown: Approximate- Landing Speed at Main Gear Touchdown: Approximate- Landing Speed at Main Gear Touchdown: Approximate- ly 202 knots (232 miles per hour) ly 202 knots (232 miles per hour) ly 202 knots (232 miles per hour) Landed: Concrete runway 15 at Kennedy Space Center, Landed: Concrete runway 15 at Kennedy Space Center, Landed: Concrete runway 15 at Kennedy Space Center, Fla. Fla. Fla. Payload: BioTube precursor experiment; SPACEHAB; Payload: BioTube precursor experiment; SPACEHAB; Payload: BioTube precursor experiment; SPACEHAB; integrated cargo carrier; mission to America’s integrated cargo carrier; mission to America’s integrated cargo carrier; mission to America’s remarkable schools; space experiment module 6; remarkable schools; space experiment module 6; remarkable schools; space experiment module 6; HTD 1403 micro wireless instrumentation system HTD 1403 micro wireless instrumentation system HTD 1403 micro wireless instrumentation system HEDS technology demonstration. HEDS technology demonstration. HEDS technology demonstration. Extravehicular Activity (EVA): Only one EVA on this Extravehicular Activity (EVA): Only one EVA on this Extravehicular Activity (EVA): Only one EVA on this mission, performed by James S. Voss and Jeffrey mission, performed by James S. Voss and Jeffrey mission, performed by James S. Voss and Jeffrey N. Williams, 6 hours, 30 minutes. During the EVA, N. Williams, 6 hours, 30 minutes. During the EVA, N. Williams, 6 hours, 30 minutes. During the EVA, Voss and Williams made the last planned equip- Voss and Williams made the last planned equip- Voss and Williams made the last planned equip- ment changes prior to the arrival of the ISS’s third ment changes prior to the arrival of the ISS’s third ment changes prior to the arrival of the ISS’s third element, Russia’s service module Zvezda. They element, Russia’s service module Zvezda. They element, Russia’s service module Zvezda. They completed assembly of a Russian crane, tested the completed assembly of a Russian crane, tested the completed assembly of a Russian crane, tested the integrity of a U.S. crane, replaced a faulty commu- integrity of a U.S. crane, replaced a faulty commu- integrity of a U.S. crane, replaced a faulty commu- nications antenna, installed handrails, and set up a nications antenna, installed handrails, and set up a nications antenna, installed handrails, and set up a camera cable. camera cable. camera cable.

Y-82 Y-82 Y-82 STS-106/2A.2b Mission Facts — Atlantis — STS-106/2A.2b Mission Facts — Atlantis — STS-106/2A.2b Mission Facts — Atlantis — Sept. 8–20, 2000 Sept. 8–20, 2000 Sept. 8–20, 2000 Commander: Terrence Wilcutt Commander: Terrence Wilcutt Commander: Terrence Wilcutt Pilot: Scott D. Altman Pilot: Scott D. Altman Pilot: Scott D. Altman Mission Specialist: Edward T. Lu Mission Specialist: Edward T. Lu Mission Specialist: Edward T. Lu Mission Specialist: Richard A. Mastracchio Mission Specialist: Richard A. Mastracchio Mission Specialist: Richard A. Mastracchio Mission Specialist: Daniel C. Burbank Mission Specialist: Daniel C. Burbank Mission Specialist: Daniel C. Burbank Mission Specialist: Yuri I. Malenchenko Mission Specialist: Yuri I. Malenchenko Mission Specialist: Yuri I. Malenchenko Mission Specialist: Boris V. Morukov Mission Specialist: Boris V. Morukov Mission Specialist: Boris V. Morukov Mission Duration: 283 hours (11 days), 19 hours, Mission Duration: 283 hours (11 days), 19 hours, Mission Duration: 283 hours (11 days), 19 hours, 11 minutes 11 minutes 11 minutes Miles Traveled: 4.9 million Miles Traveled: 4.9 million Miles Traveled: 4.9 million Inclination: 51.6 degrees Inclination: 51.6 degrees Inclination: 51.6 degrees Orbits of Earth: 185 Orbits of Earth: 185 Orbits of Earth: 185 Orbital Altitude: 177 nautical miles (approximately Orbital Altitude: 177 nautical miles (approximately Orbital Altitude: 177 nautical miles (approximately 203 statute miles) 203 statute miles) 203 statute miles) Orbiter Weight at Landing: 221,803 pounds Orbiter Weight at Landing: 221,803 pounds Orbiter Weight at Landing: 221,803 pounds Lift-Off Weight: 4,519,178 pounds Lift-Off Weight: 4,519,178 pounds Lift-Off Weight: 4,519,178 pounds Orbiter Weight at Lift-Off: 262,053 pounds Orbiter Weight at Lift-Off: 262,053 pounds Orbiter Weight at Lift-Off: 262,053 pounds Payload Weight Up: 23,967 pounds Payload Weight Up: 23,967 pounds Payload Weight Up: 23,967 pounds Payload Weight Down: 20,173 pounds Payload Weight Down: 20,173 pounds Payload Weight Down: 20,173 pounds Landing Touchdown: Approximately 3,066 feet beyond Landing Touchdown: Approximately 3,066 feet beyond Landing Touchdown: Approximately 3,066 feet beyond threshold threshold threshold Landing Rollout: Approximately 9,115 feet Landing Rollout: Approximately 9,115 feet Landing Rollout: Approximately 9,115 feet Landing Speed at Main Gear Touchdown: Approximate- Landing Speed at Main Gear Touchdown: Approximate- Landing Speed at Main Gear Touchdown: Approximate- ly 187 knots (215 miles per hour) ly 187 knots (215 miles per hour) ly 187 knots (215 miles per hour) Landed: Concrete runway 15 at Kennedy Space Center, Landed: Concrete runway 15 at Kennedy Space Center, Landed: Concrete runway 15 at Kennedy Space Center, Fla. Fla. Fla. Payload: Space Experiment Module 8; Getaway Special Payload: Space Experiment Module 8; Getaway Special Payload: Space Experiment Module 8; Getaway Special G-782, SPACEHAB Logistics Double Module (in G-782, SPACEHAB Logistics Double Module (in G-782, SPACEHAB Logistics Double Module (in cargo bay); Commercial Generic Bioprocessing cargo bay); Commercial Generic Bioprocessing cargo bay); Commercial Generic Bioprocessing Apparatus (in-cabin). Apparatus (in-cabin). Apparatus (in-cabin). Extravehicular Activity (EVA): EVA 1, Mission Special- Extravehicular Activity (EVA): EVA 1, Mission Special- Extravehicular Activity (EVA): EVA 1, Mission Special- ists Dr. Edward Lu and Col. Yuri Malenchenko, ists Dr. Edward Lu and Col. Yuri Malenchenko, ists Dr. Edward Lu and Col. Yuri Malenchenko, 6 hours, 14 minutes. This was the sixth space walk 6 hours, 14 minutes. This was the sixth space walk 6 hours, 14 minutes. This was the sixth space walk in support of the assembly of the ISS and the 50th in support of the assembly of the ISS and the 50th in support of the assembly of the ISS and the 50th in Shuttle history. During the EVA, the two made in Shuttle history. During the EVA, the two made in Shuttle history. During the EVA, the two made the grueling ascent to lay cable and install a boom the grueling ascent to lay cable and install a boom the grueling ascent to lay cable and install a boom for a navigation unit on the exterior of the ISS. They for a navigation unit on the exterior of the ISS. They for a navigation unit on the exterior of the ISS. They ventured 110 feet from the Shuttle cargo bay, the ventured 110 feet from the Shuttle cargo bay, the ventured 110 feet from the Shuttle cargo bay, the farthest distance any NASA spacewalker has ever farthest distance any NASA spacewalker has ever farthest distance any NASA spacewalker has ever ventured while tethered. They had to scale the Rus- ventured while tethered. They had to scale the Rus- ventured while tethered. They had to scale the Rus- sian service module Zvezda to erect the boom for a sian service module Zvezda to erect the boom for a sian service module Zvezda to erect the boom for a compass and to install the cables between Zvezda compass and to install the cables between Zvezda compass and to install the cables between Zvezda and the other Russian module, Zarya. and the other Russian module, Zarya. and the other Russian module, Zarya.

STS-92 Mission Facts — Discovery — STS-92 Mission Facts — Discovery — STS-92 Mission Facts — Discovery — Oct. 11–24, 2000 Oct. 11–24, 2000 Oct. 11–24, 2000

Commander: Brian Duffy Commander: Brian Duffy Commander: Brian Duffy Pilot: Pamela Ann Melroy Pilot: Pamela Ann Melroy Pilot: Pamela Ann Melroy Mission Specialist: Koichi Wakata, National Space Mission Specialist: Koichi Wakata, National Space Mission Specialist: Koichi Wakata, National Space Development Agency of Japan Development Agency of Japan Development Agency of Japan Mission Specialist: Peter J.K. (Jeff) Wisoff Mission Specialist: Peter J.K. (Jeff) Wisoff Mission Specialist: Peter J.K. (Jeff) Wisoff

Y-83 Y-83 Y-83 STS-92 Mission Facts (Cont) STS-92 Mission Facts (Cont) STS-92 Mission Facts (Cont)

Mission Specialist: Leroy Chiao Mission Specialist: Leroy Chiao Mission Specialist: Leroy Chiao Mission Specialist: William S. McArthur, Jr. Mission Specialist: William S. McArthur, Jr. Mission Specialist: William S. McArthur, Jr. Mission Specialist: Michael E. Lopez-Alegria Mission Specialist: Michael E. Lopez-Alegria Mission Specialist: Michael E. Lopez-Alegria Mission Duration: 288 hours (12 days), 21 hours, Mission Duration: 288 hours (12 days), 21 hours, Mission Duration: 288 hours (12 days), 21 hours, 43 minutes, 47 seconds 43 minutes, 47 seconds 43 minutes, 47 seconds Miles Traveled: Approximately 5.3 million statute miles Miles Traveled: Approximately 5.3 million statute miles Miles Traveled: Approximately 5.3 million statute miles Inclination: 51.6 degrees Inclination: 51.6 degrees Inclination: 51.6 degrees Orbits of Earth: 203 Orbits of Earth: 203 Orbits of Earth: 203 Orbital Altitude: 173 nautical miles (approximately Orbital Altitude: 173 nautical miles (approximately Orbital Altitude: 173 nautical miles (approximately 259 statute miles) 259 statute miles) 259 statute miles) Orbiter Weight at Landing: 204,455 pounds Orbiter Weight at Landing: 204,455 pounds Orbiter Weight at Landing: 204,455 pounds Lift-Off Weight: Approximately 4,520,596 pounds Lift-Off Weight: Approximately 4,520,596 pounds Lift-Off Weight: Approximately 4,520,596 pounds Orbiter Weight at Lift-Off: 253,807 pounds Orbiter Weight at Lift-Off: 253,807 pounds Orbiter Weight at Lift-Off: 253,807 pounds Payload Weight Up: 28,009 pounds Payload Weight Up: 28,009 pounds Payload Weight Up: 28,009 pounds Payload Weight Down: 6,304 pounds Payload Weight Down: 6,304 pounds Payload Weight Down: 6,304 pounds Landing Touchdown: Approximately 2,771 feet beyond Landing Touchdown: Approximately 2,771 feet beyond Landing Touchdown: Approximately 2,771 feet beyond threshold threshold threshold Landing Rollout: Approximately 9,087 feet Landing Rollout: Approximately 9,087 feet Landing Rollout: Approximately 9,087 feet Landing Speed at Main Gear Touchdown: Approximately Landing Speed at Main Gear Touchdown: Approximately Landing Speed at Main Gear Touchdown: Approximately 205 knots (236 miles per hour) 205 knots (236 miles per hour) 205 knots (236 miles per hour) Landed: Concrete runway 22 at Edwards Air Force Base, Landed: Concrete runway 22 at Edwards Air Force Base, Landed: Concrete runway 22 at Edwards Air Force Base, California California California Payload: International Space Station (3A); Z1 truss; pres- Payload: International Space Station (3A); Z1 truss; pres- Payload: International Space Station (3A); Z1 truss; pres- surized mating adapter 3 (PMA-3); five DTOs; cargo surized mating adapter 3 (PMA-3); five DTOs; cargo surized mating adapter 3 (PMA-3); five DTOs; cargo transfer. transfer. transfer. Extravehicular Activity (EVA): EVA 1, Mission Specialists Extravehicular Activity (EVA): EVA 1, Mission Specialists Extravehicular Activity (EVA): EVA 1, Mission Specialists Leroy Chiao and William McArthur, 6 hours, 28 min- Leroy Chiao and William McArthur, 6 hours, 28 min- Leroy Chiao and William McArthur, 6 hours, 28 min- utes. During EVA 1, Chiao and McArthur relocated utes. During EVA 1, Chiao and McArthur relocated utes. During EVA 1, Chiao and McArthur relocated the S-band antenna support assembly on the Z1 the S-band antenna support assembly on the Z1 the S-band antenna support assembly on the Z1 truss and connected Z1-to-Unity umbilicals. EVA 2, truss and connected Z1-to-Unity umbilicals. EVA 2, truss and connected Z1-to-Unity umbilicals. EVA 2, Mission Specialists Jeff Wisoff and Michael Lopez- Mission Specialists Jeff Wisoff and Michael Lopez- Mission Specialists Jeff Wisoff and Michael Lopez- Alegria, 7 hours, 7 minutes. During EVA 2, Koichi Alegria, 7 hours, 7 minutes. During EVA 2, Koichi Alegria, 7 hours, 7 minutes. During EVA 2, Koichi Wakata used the shuttle’s robotic arm to grapple Wakata used the shuttle’s robotic arm to grapple Wakata used the shuttle’s robotic arm to grapple and install PMA-3 on Unity’s nadir port. Wisoff and and install PMA-3 on Unity’s nadir port. Wisoff and and install PMA-3 on Unity’s nadir port. Wisoff and Lopez-Alegria connected cables between PMA-3 Lopez-Alegria connected cables between PMA-3 Lopez-Alegria connected cables between PMA-3 and Unity. EVA 3, Mission Specialists Chiao and and Unity. EVA 3, Mission Specialists Chiao and and Unity. EVA 3, Mission Specialists Chiao and McArthur, 6 hours, 48 minutes. During EVA 3, Chiao McArthur, 6 hours, 48 minutes. During EVA 3, Chiao McArthur, 6 hours, 48 minutes. During EVA 3, Chiao and McArthur installed two DC-to-DC converter unit and McArthur installed two DC-to-DC converter unit and McArthur installed two DC-to-DC converter unit heat pipes on the Z1 truss and relocated the Z1 keel heat pipes on the Z1 truss and relocated the Z1 keel heat pipes on the Z1 truss and relocated the Z1 keel pin assembly. EVA 4, Mission Specialists Wisoff and pin assembly. EVA 4, Mission Specialists Wisoff and pin assembly. EVA 4, Mission Specialists Wisoff and Lopez-Alegria, 6 hours, 56 minutes. During EVA 4, Lopez-Alegria, 6 hours, 56 minutes. During EVA 4, Lopez-Alegria, 6 hours, 56 minutes. During EVA 4, Wisoff and Lopez-Alegria removed a grapple fixture Wisoff and Lopez-Alegria removed a grapple fixture Wisoff and Lopez-Alegria removed a grapple fixture on the Z1 truss. Wisoff and Lopez-Alegria also on the Z1 truss. Wisoff and Lopez-Alegria also on the Z1 truss. Wisoff and Lopez-Alegria also performed a safety protocol test, a flight evaluation performed a safety protocol test, a flight evaluation performed a safety protocol test, a flight evaluation of simplified aid for EVA rescue (SAFER). of simplified aid for EVA rescue (SAFER). of simplified aid for EVA rescue (SAFER).

100th Space Shuttle mission 100th Space Shuttle mission 100th Space Shuttle mission

Y-84 Y-84 Y-84 STS-97 Mission Facts — Endeavour — STS-97 Mission Facts — Endeavour — STS-97 Mission Facts — Endeavour — Nov. 30–Dec. 11, 2000 Nov. 30–Dec. 11, 2000 Nov. 30–Dec. 11, 2000 Commander: Brent W. Jett Jr. Commander: Brent W. Jett Jr. Commander: Brent W. Jett Jr. Pilot: Michael J. Bloomfield Pilot: Michael J. Bloomfield Pilot: Michael J. Bloomfield Mission Specialist: Marc Garneau, Canadian Space Mission Specialist: Marc Garneau, Canadian Space Mission Specialist: Marc Garneau, Canadian Space Agency Agency Agency Mission Specialist: Joseph R. Tanner Mission Specialist: Joseph R. Tanner Mission Specialist: Joseph R. Tanner Mission Specialist: Carlos I. Noriega Mission Specialist: Carlos I. Noriega Mission Specialist: Carlos I. Noriega Mission Duration: 240 hours (10 days), 19 hours, 58 min- Mission Duration: 240 hours (10 days), 19 hours, 58 min- Mission Duration: 240 hours (10 days), 19 hours, 58 min- utes utes utes Miles Traveled: Approximately 4.47 million statute miles Miles Traveled: Approximately 4.47 million statute miles Miles Traveled: Approximately 4.47 million statute miles Inclination: 51.6 degrees Inclination: 51.6 degrees Inclination: 51.6 degrees Orbits of Earth: 170 Orbits of Earth: 170 Orbits of Earth: 170 Orbital Altitude: 173 nautical miles (approximately 259 Orbital Altitude: 173 nautical miles (approximately 259 Orbital Altitude: 173 nautical miles (approximately 259 statute miles) statute miles) statute miles) Orbital ISS Rendezvous Altitude: 205 nautical miles (ap- Orbital ISS Rendezvous Altitude: 205 nautical miles (ap- Orbital ISS Rendezvous Altitude: 205 nautical miles (ap- proximately 307 statute miles) proximately 307 statute miles) proximately 307 statute miles) Orbiter Weight at Landing: 197,377 pounds Orbiter Weight at Landing: 197,377 pounds Orbiter Weight at Landing: 197,377 pounds Lift-Off Weight: 4,524,795 pounds Lift-Off Weight: 4,524,795 pounds Lift-Off Weight: 4,524,795 pounds Orbiter Weight at Lift-Off: 266,570 pounds Orbiter Weight at Lift-Off: 266,570 pounds Orbiter Weight at Lift-Off: 266,570 pounds Payload Weight Up: 37,496 pounds Payload Weight Up: 37,496 pounds Payload Weight Up: 37,496 pounds Payload Weight Down: 1,920 pounds Payload Weight Down: 1,920 pounds Payload Weight Down: 1,920 pounds Landing Touchdown: Approximately 2,476 feet beyond Landing Touchdown: Approximately 2,476 feet beyond Landing Touchdown: Approximately 2,476 feet beyond threshold threshold threshold Landing Rollout: Approximately 7,961 feet Landing Rollout: Approximately 7,961 feet Landing Rollout: Approximately 7,961 feet Landing Speed at Main Gear Touchdown: Approximately Landing Speed at Main Gear Touchdown: Approximately Landing Speed at Main Gear Touchdown: Approximately 195 knots (224 miles per hour) 195 knots (224 miles per hour) 195 knots (224 miles per hour) Landed: Concrete runway 15 at Kennedy Space Center, Landed: Concrete runway 15 at Kennedy Space Center, Landed: Concrete runway 15 at Kennedy Space Center, Fla. Fla. Fla. Payload: International Space Station (4A); P6 photovoltaic Payload: International Space Station (4A); P6 photovoltaic Payload: International Space Station (4A); P6 photovoltaic array assembly; integrated equipment assembly; array assembly; integrated equipment assembly; array assembly; integrated equipment assembly; five DTOs, one DSO, and two HTDs. five DTOs, one DSO, and two HTDs. five DTOs, one DSO, and two HTDs. Extravehicular Activity (EVA): EVA 1, Mission Specialists Extravehicular Activity (EVA): EVA 1, Mission Specialists Extravehicular Activity (EVA): EVA 1, Mission Specialists Joseph Tanner and Carlos Noriega, 7 hours, 33 min- Joseph Tanner and Carlos Noriega, 7 hours, 33 min- Joseph Tanner and Carlos Noriega, 7 hours, 33 min- utes. During EVA 1, Tanner and Noriega attached utes. During EVA 1, Tanner and Noriega attached utes. During EVA 1, Tanner and Noriega attached the P6 integrated truss structure to the Z1 truss, pre- the P6 integrated truss structure to the Z1 truss, pre- the P6 integrated truss structure to the Z1 truss, pre- pared the solar arrays for deployment, and prepared pared the solar arrays for deployment, and prepared pared the solar arrays for deployment, and prepared the radiator for power system deployment. EVA 2, the radiator for power system deployment. EVA 2, the radiator for power system deployment. EVA 2, Tanner and Noriega, 6 hours, 37 minutes. During Tanner and Noriega, 6 hours, 37 minutes. During Tanner and Noriega, 6 hours, 37 minutes. During EVA 2, Tanner and Noriega configured the ISS for EVA 2, Tanner and Noriega configured the ISS for EVA 2, Tanner and Noriega configured the ISS for use of the power from the P6, positioned the S-band use of the power from the P6, positioned the S-band use of the power from the P6, positioned the S-band for use by the space station, and prepared the ISS for use by the space station, and prepared the ISS for use by the space station, and prepared the ISS for the arrival of the U.S. Laboratory on mission ISS- for the arrival of the U.S. Laboratory on mission ISS- for the arrival of the U.S. Laboratory on mission ISS- 5A. EVA 3, Tanner and Noriega, 5 hours, 10 minutes. 5A. EVA 3, Tanner and Noriega, 5 hours, 10 minutes. 5A. EVA 3, Tanner and Noriega, 5 hours, 10 minutes. During EVA 3, Tanner and Noriega performed repair During EVA 3, Tanner and Noriega performed repair During EVA 3, Tanner and Noriega performed repair work to increase tension in the starboard solar array work to increase tension in the starboard solar array work to increase tension in the starboard solar array blankets and performed get-ahead tasks that were blankets and performed get-ahead tasks that were blankets and performed get-ahead tasks that were planned for future space station assembly missions. planned for future space station assembly missions. planned for future space station assembly missions.

Y-85 Y-85 Y-85 STS-98 Mission Facts — Atlantis — STS-98 Mission Facts — Atlantis — STS-98 Mission Facts — Atlantis — Feb. 7–20, 2001 Feb. 7–20, 2001 Feb. 7–20, 2001 Commander: Kenneth D. Cockrell Commander: Kenneth D. Cockrell Commander: Kenneth D. Cockrell Pilot: Mark L. Polansky Pilot: Mark L. Polansky Pilot: Mark L. Polansky Mission Specialist: Marsha Ivins Mission Specialist: Marsha Ivins Mission Specialist: Marsha Ivins Mission Specialist: Thomas D. Jones Mission Specialist: Thomas D. Jones Mission Specialist: Thomas D. Jones Mission Specialist: Robert L. Curbeam Jr. Mission Specialist: Robert L. Curbeam Jr. Mission Specialist: Robert L. Curbeam Jr. Mission Duration: 288 hours (12 days), 21 hours, Mission Duration: 288 hours (12 days), 21 hours, Mission Duration: 288 hours (12 days), 21 hours, 20 minutes 20 minutes 20 minutes Miles Traveled: Approximately 5.3 million statute miles Miles Traveled: Approximately 5.3 million statute miles Miles Traveled: Approximately 5.3 million statute miles Inclination: 51.6 degrees Inclination: 51.6 degrees Inclination: 51.6 degrees Orbits of Earth: 203 Orbits of Earth: 203 Orbits of Earth: 203 Orbital Altitude: 177 nautical miles Orbital Altitude: 177 nautical miles Orbital Altitude: 177 nautical miles Orbital ISS Rendezvous Altitude: Approximately Orbital ISS Rendezvous Altitude: Approximately Orbital ISS Rendezvous Altitude: Approximately 200 nautical miles 200 nautical miles 200 nautical miles Orbiter Weight at Landing: 198,849 pounds Orbiter Weight at Landing: 198,849 pounds Orbiter Weight at Landing: 198,849 pounds Lift-Off Weight: Approximately 4.5 million pounds Lift-Off Weight: Approximately 4.5 million pounds Lift-Off Weight: Approximately 4.5 million pounds Orbiter Weight at Lift-Off: 264,127 pounds Orbiter Weight at Lift-Off: 264,127 pounds Orbiter Weight at Lift-Off: 264,127 pounds Payload Weight Up: 33,286 pounds Payload Weight Up: 33,286 pounds Payload Weight Up: 33,286 pounds Payload Weight Down: 2,673 pounds Payload Weight Down: 2,673 pounds Payload Weight Down: 2,673 pounds Landing Touchdown: Approximately 2,095 feet beyond Landing Touchdown: Approximately 2,095 feet beyond Landing Touchdown: Approximately 2,095 feet beyond threshold threshold threshold Landing Rollout: Approximately 7,964 feet Landing Rollout: Approximately 7,964 feet Landing Rollout: Approximately 7,964 feet Landing Speed at Main Gear Touchdown: Approximately Landing Speed at Main Gear Touchdown: Approximately Landing Speed at Main Gear Touchdown: Approximately 198 knots (228 miles per hour) 198 knots (228 miles per hour) 198 knots (228 miles per hour) Landed: Concrete runway 22 at Edwards Air Force Base, Landed: Concrete runway 22 at Edwards Air Force Base, Landed: Concrete runway 22 at Edwards Air Force Base, Calif. Calif. Calif. Payload: ISS Assembly Flight 5A; U.S. Laboratory Module Payload: ISS Assembly Flight 5A; U.S. Laboratory Module Payload: ISS Assembly Flight 5A; U.S. Laboratory Module “Destiny” “Destiny” “Destiny” Extravehicular Activity (EVAs): EVA 1, mission specialists Extravehicular Activity (EVAs): EVA 1, mission specialists Extravehicular Activity (EVAs): EVA 1, mission specialists Bob Curbeam and Tom Jones, 7 hours, 34 minutes, Bob Curbeam and Tom Jones, 7 hours, 34 minutes, Bob Curbeam and Tom Jones, 7 hours, 34 minutes, Curbeam and Jones installed and hooked up Curbeam and Jones installed and hooked up Curbeam and Jones installed and hooked up Destiny to ISS's Unity module. EVA 2, Curbeam and Destiny to ISS's Unity module. EVA 2, Curbeam and Destiny to ISS's Unity module. EVA 2, Curbeam and Jones, 6 hours, 50 minutes. Curbeam and Jones Jones, 6 hours, 50 minutes. Curbeam and Jones Jones, 6 hours, 50 minutes. Curbeam and Jones attached a station docking adapter to the forward attached a station docking adapter to the forward attached a station docking adapter to the forward end of Destiny to establish a new docking port for end of Destiny to establish a new docking port for end of Destiny to establish a new docking port for future Shuttle assembly flights. EVA 3, Curbeam future Shuttle assembly flights. EVA 3, Curbeam future Shuttle assembly flights. EVA 3, Curbeam and Jones, 5 hours, 25 minutes, the 100th space- and Jones, 5 hours, 25 minutes, the 100th space- and Jones, 5 hours, 25 minutes, the 100th space- walk in U.S. space program history. Curbeam and walk in U.S. space program history. Curbeam and walk in U.S. space program history. Curbeam and Jones attached a spare communications antenna Jones attached a spare communications antenna Jones attached a spare communications antenna on the exterior of the ISS and inspected the exterior on the exterior of the ISS and inspected the exterior on the exterior of the ISS and inspected the exterior of the ISS and the U.S. solar arrays. of the ISS and the U.S. solar arrays. of the ISS and the U.S. solar arrays.

STS-102 Mission Facts — Discovery — STS-102 Mission Facts — Discovery — STS-102 Mission Facts — Discovery — March 8–21, 2001 March 8–21, 2001 March 8–21, 2001

Commander: James D. Weatherbee Commander: James D. Weatherbee Commander: James D. Weatherbee Pilot: James M. Kelly Pilot: James M. Kelly Pilot: James M. Kelly Mission Specialist: Andrew S.W. Thomas Mission Specialist: Andrew S.W. Thomas Mission Specialist: Andrew S.W. Thomas Mission Specialist: Paul W. Richards Mission Specialist: Paul W. Richards Mission Specialist: Paul W. Richards ISS Crew Member: Yury V. Usachev—up only ISS Crew Member: Yury V. Usachev—up only ISS Crew Member: Yury V. Usachev—up only ISS Crew Member: Susan J. Helms—up only ISS Crew Member: Susan J. Helms—up only ISS Crew Member: Susan J. Helms—up only

Y-86 Y-86 Y-86 STS-102 Mission Facts (Cont) STS-102 Mission Facts (Cont) STS-102 Mission Facts (Cont) ISS Crew Member: James S. Voss—up only ISS Crew Member: James S. Voss—up only ISS Crew Member: James S. Voss—up only ISS Crew Member: William M. Shepherd—down only ISS Crew Member: William M. Shepherd—down only ISS Crew Member: William M. Shepherd—down only ISS Crew Member: Sergei K. Krikalev—down only ISS Crew Member: Sergei K. Krikalev—down only ISS Crew Member: Sergei K. Krikalev—down only ISS Crew Member: Yuri P. Gidzenko—down only ISS Crew Member: Yuri P. Gidzenko—down only ISS Crew Member: Yuri P. Gidzenko—down only Mission Duration: 288 hours (12 days), 19 hours, Mission Duration: 288 hours (12 days), 19 hours, Mission Duration: 288 hours (12 days), 19 hours, 49 minutes 49 minutes 49 minutes Miles Traveled: Approximately 5.4 million statute miles Miles Traveled: Approximately 5.4 million statute miles Miles Traveled: Approximately 5.4 million statute miles Inclination: 51.6 degrees Inclination: 51.6 degrees Inclination: 51.6 degrees Orbits of Earth: 202 Orbits of Earth: 202 Orbits of Earth: 202 Orbital Altitude: 122 nautical miles (approximately Orbital Altitude: 122 nautical miles (approximately Orbital Altitude: 122 nautical miles (approximately 140 statute miles) 140 statute miles) 140 statute miles) Orbital ISS Rendezvous Altitude: 205 nautical miles Orbital ISS Rendezvous Altitude: 205 nautical miles Orbital ISS Rendezvous Altitude: 205 nautical miles Orbiter Weight at Landing: 217,771 pounds Orbiter Weight at Landing: 217,771 pounds Orbiter Weight at Landing: 217,771 pounds Lift-Off Weight: Approximately 4.5 million pounds Lift-Off Weight: Approximately 4.5 million pounds Lift-Off Weight: Approximately 4.5 million pounds Orbiter Weight at Lift-Off: 264,797 pounds Orbiter Weight at Lift-Off: 264,797 pounds Orbiter Weight at Lift-Off: 264,797 pounds Payload Weight Up: 28,739 pounds Payload Weight Up: 28,739 pounds Payload Weight Up: 28,739 pounds Payload Weight Down: 20,389 pounds Payload Weight Down: 20,389 pounds Payload Weight Down: 20,389 pounds Landing Touchdown: Approximately 2,952 feet beyond Landing Touchdown: Approximately 2,952 feet beyond Landing Touchdown: Approximately 2,952 feet beyond threshold threshold threshold Landing Rollout: Approximately 11,409 feet Landing Rollout: Approximately 11,409 feet Landing Rollout: Approximately 11,409 feet Landing Speed at Main Gear Touchdown: Approximately Landing Speed at Main Gear Touchdown: Approximately Landing Speed at Main Gear Touchdown: Approximately 199 knots (229 miles per hour) 199 knots (229 miles per hour) 199 knots (229 miles per hour) Landed: Concrete runway 15 at Kennedy Space Center, Landed: Concrete runway 15 at Kennedy Space Center, Landed: Concrete runway 15 at Kennedy Space Center, Fla. Fla. Fla. Payload: ISS Assembly Flight 5A.1; Leonardo Multi- Payload: ISS Assembly Flight 5A.1; Leonardo Multi- Payload: ISS Assembly Flight 5A.1; Leonardo Multi- Purpose Logistics Module; External Stowage Purpose Logistics Module; External Stowage Purpose Logistics Module; External Stowage Platform 1 Platform 1 Platform 1 Extravehicular Activity (EVAs): EVA 1, Susan Helms and Extravehicular Activity (EVAs): EVA 1, Susan Helms and Extravehicular Activity (EVAs): EVA 1, Susan Helms and Jim Voss, 8 hours, 56 minutes. Helms and Voss pre- Jim Voss, 8 hours, 56 minutes. Helms and Voss pre- Jim Voss, 8 hours, 56 minutes. Helms and Voss pre- pared one of ISS’s berthing ports for the Leonardo pared one of ISS’s berthing ports for the Leonardo pared one of ISS’s berthing ports for the Leonardo transfer module. EVA 2, Paul Richards and Andy transfer module. EVA 2, Paul Richards and Andy transfer module. EVA 2, Paul Richards and Andy Thomas, 6 hours, 30 minutes. Richards and Thomas Thomas, 6 hours, 30 minutes. Richards and Thomas Thomas, 6 hours, 30 minutes. Richards and Thomas continued work to outfit the station and prepare for continued work to outfit the station and prepare for continued work to outfit the station and prepare for delivery of its own robotic arm on the next mission. delivery of its own robotic arm on the next mission. delivery of its own robotic arm on the next mission.

STS-100 Mission Facts — Endeavour — STS-100 Mission Facts — Endeavour — STS-100 Mission Facts — Endeavour — April 19–May 1, 2001 April 19–May 1, 2001 April 19–May 1, 2001

Commander: Kent V. Rominger Commander: Kent V. Rominger Commander: Kent V. Rominger Pilot: Jeffrey S. Ashby Pilot: Jeffrey S. Ashby Pilot: Jeffrey S. Ashby Mission Specialist: Chris A. Hadfield, Canadian Space Mission Specialist: Chris A. Hadfield, Canadian Space Mission Specialist: Chris A. Hadfield, Canadian Space Agency Agency Agency Mission Specialist: John L. Phillips Mission Specialist: John L. Phillips Mission Specialist: John L. Phillips Mission Specialist: Scott E. Parazynski Mission Specialist: Scott E. Parazynski Mission Specialist: Scott E. Parazynski Mission Specialist: Umberto Guidoni, European Space Mission Specialist: Umberto Guidoni, European Space Mission Specialist: Umberto Guidoni, European Space Agency Agency Agency Mission Specialist: Yuri Valentinovich Lonchakov, Russian Mission Specialist: Yuri Valentinovich Lonchakov, Russian Mission Specialist: Yuri Valentinovich Lonchakov, Russian Air Force Air Force Air Force Mission Duration: 264 hours (11 days), 21 hours, Mission Duration: 264 hours (11 days), 21 hours, Mission Duration: 264 hours (11 days), 21 hours, 30 minutes 30 minutes 30 minutes Miles Traveled: Approximately 4.9 million statute miles Miles Traveled: Approximately 4.9 million statute miles Miles Traveled: Approximately 4.9 million statute miles Inclination: 51.6 degrees Inclination: 51.6 degrees Inclination: 51.6 degrees

Y-87 Y-87 Y-87 STS-100 Mission Facts (Cont) STS-100 Mission Facts (Cont) STS-100 Mission Facts (Cont) Orbits of Earth: 186 Orbits of Earth: 186 Orbits of Earth: 186 Orbital Altitude: 173 nautical miles (approximately Orbital Altitude: 173 nautical miles (approximately Orbital Altitude: 173 nautical miles (approximately 259 statute miles) 259 statute miles) 259 statute miles) Orbital ISS Rendezvous Altitude: 240 nautical miles Orbital ISS Rendezvous Altitude: 240 nautical miles Orbital ISS Rendezvous Altitude: 240 nautical miles Orbiter Weight at Landing: 220,125 pounds Orbiter Weight at Landing: 220,125 pounds Orbiter Weight at Landing: 220,125 pounds Lift-Off Weight: 4,522,246 pounds Lift-Off Weight: 4,522,246 pounds Lift-Off Weight: 4,522,246 pounds Orbiter Weight at Lift-Off: 265,268 pounds Orbiter Weight at Lift-Off: 265,268 pounds Orbiter Weight at Lift-Off: 265,268 pounds Payload Weight Up: 29,472 pounds Payload Weight Up: 29,472 pounds Payload Weight Up: 29,472 pounds Payload Weight Down: 20,346 pounds Payload Weight Down: 20,346 pounds Payload Weight Down: 20,346 pounds Landing Touchdown: Approximately 2,219 feet beyond Landing Touchdown: Approximately 2,219 feet beyond Landing Touchdown: Approximately 2,219 feet beyond threshold threshold threshold Landing Rollout: Approximately 7,992 feet Landing Rollout: Approximately 7,992 feet Landing Rollout: Approximately 7,992 feet Landing Speed at Main Gear Touchdown: Approximately Landing Speed at Main Gear Touchdown: Approximately Landing Speed at Main Gear Touchdown: Approximately 207 knots (238 miles per hour) 207 knots (238 miles per hour) 207 knots (238 miles per hour) Landed: Concrete runway 22 at Edwards Air Force Base, Landed: Concrete runway 22 at Edwards Air Force Base, Landed: Concrete runway 22 at Edwards Air Force Base, Calif. Calif. Calif. Payload: ISS Assembly Flight 6A; Raffaello Multi-Purpose Payload: ISS Assembly Flight 6A; Raffaello Multi-Purpose Payload: ISS Assembly Flight 6A; Raffaello Multi-Purpose Logistics Module, Space Station Remote Manipula- Logistics Module, Space Station Remote Manipula- Logistics Module, Space Station Remote Manipula- tor System (SSRMS), also known as Canadarm2, tor System (SSRMS), also known as Canadarm2, tor System (SSRMS), also known as Canadarm2, UHF antenna UHF antenna UHF antenna Extravehicular Activity (EVAs) conducted by Scott Extravehicular Activity (EVAs) conducted by Scott Extravehicular Activity (EVAs) conducted by Scott Parazynski and Chris Hadfield. EVA 1, 7 hours, Parazynski and Chris Hadfield. EVA 1, 7 hours, Parazynski and Chris Hadfield. EVA 1, 7 hours, 10 minutes, Parazynski and Hadfield installed and 10 minutes, Parazynski and Hadfield installed and 10 minutes, Parazynski and Hadfield installed and deployed the UHF antenna on Destiny and began deployed the UHF antenna on Destiny and began deployed the UHF antenna on Destiny and began installation of Canadarm2. EVA 2, 7 hours, 40 installation of Canadarm2. EVA 2, 7 hours, 40 installation of Canadarm2. EVA 2, 7 hours, 40 minutes, Parazynski and Hadfield completed power minutes, Parazynski and Hadfield completed power minutes, Parazynski and Hadfield completed power and data connections on Canadarm2. and data connections on Canadarm2. and data connections on Canadarm2.

STS-104 Mission Facts — Atlantis — STS-104 Mission Facts — Atlantis — STS-104 Mission Facts — Atlantis — July 12–24, 2001 July 12–24, 2001 July 12–24, 2001

Commander: Steven W. Lindsey Commander: Steven W. Lindsey Commander: Steven W. Lindsey Pilot: Charles O. Hobaugh Pilot: Charles O. Hobaugh Pilot: Charles O. Hobaugh Mission Specialist: Michael L. Gernhardt Mission Specialist: Michael L. Gernhardt Mission Specialist: Michael L. Gernhardt Mission Specialist: James F. Reilly Mission Specialist: James F. Reilly Mission Specialist: James F. Reilly Mission Specialist: Janet L. Kavandi Mission Specialist: Janet L. Kavandi Mission Specialist: Janet L. Kavandi Mission Duration: 288 hours (12 days), 18 hours, Mission Duration: 288 hours (12 days), 18 hours, Mission Duration: 288 hours (12 days), 18 hours, 35 minutes 35 minutes 35 minutes Miles Traveled: Approximately 5.3 million statute miles Miles Traveled: Approximately 5.3 million statute miles Miles Traveled: Approximately 5.3 million statute miles Inclination: 51.6 degrees Inclination: 51.6 degrees Inclination: 51.6 degrees Orbits of Earth: 200 Orbits of Earth: 200 Orbits of Earth: 200 Orbital Insertion Altitude: 122 nautical miles Orbital Insertion Altitude: 122 nautical miles Orbital Insertion Altitude: 122 nautical miles Orbital ISS Rendezvous Altitude: 240 nautical miles Orbital ISS Rendezvous Altitude: 240 nautical miles Orbital ISS Rendezvous Altitude: 240 nautical miles Orbiter Weight at Landing: 206,902 pounds Orbiter Weight at Landing: 206,902 pounds Orbiter Weight at Landing: 206,902 pounds Lift-Off Weight: 4,520,159 pounds Lift-Off Weight: 4,520,159 pounds Lift-Off Weight: 4,520,159 pounds Orbiter Weight at Lift-Off: 262,952 pounds Orbiter Weight at Lift-Off: 262,952 pounds Orbiter Weight at Lift-Off: 262,952 pounds Payload Weight Up: 26,424 pounds Payload Weight Up: 26,424 pounds Payload Weight Up: 26,424 pounds Payload Weight Down: 7,268 pounds Payload Weight Down: 7,268 pounds Payload Weight Down: 7,268 pounds Landing Touchdown: Approximately 2,273 feet beyond Landing Touchdown: Approximately 2,273 feet beyond Landing Touchdown: Approximately 2,273 feet beyond threshold threshold threshold

Y-88 Y-88 Y-88 STS-104 Mission Facts (Cont) STS-104 Mission Facts (Cont) STS-104 Mission Facts (Cont) Landing Rollout: Approximately 10,854 feet Landing Rollout: Approximately 10,854 feet Landing Rollout: Approximately 10,854 feet Landing Speed at Main Gear Touchdown: Approximately Landing Speed at Main Gear Touchdown: Approximately Landing Speed at Main Gear Touchdown: Approximately 198 knots (228 miles per hour) 198 knots (228 miles per hour) 198 knots (228 miles per hour) Landed: Concrete runway 15 at Kennedy Space Center, Landed: Concrete runway 15 at Kennedy Space Center, Landed: Concrete runway 15 at Kennedy Space Center, Fla. Fla. Fla. Payload: ISS Assembly Flight 7A; Joint Airlock and Payload: ISS Assembly Flight 7A; Joint Airlock and Payload: ISS Assembly Flight 7A; Joint Airlock and High-Pressure Gas Tanks; first flight of Block II main High-Pressure Gas Tanks; first flight of Block II main High-Pressure Gas Tanks; first flight of Block II main engine high-pressure fuel turbopump engine high-pressure fuel turbopump engine high-pressure fuel turbopump Extravehicular Activity (EVAs) conducted by Michael Extravehicular Activity (EVAs) conducted by Michael Extravehicular Activity (EVAs) conducted by Michael Gernhardt and James Reilly. EVA 1, 5 hours, 59 Gernhardt and James Reilly. EVA 1, 5 hours, 59 Gernhardt and James Reilly. EVA 1, 5 hours, 59 minutes, Gernhardt and Reilly assisted space station minutes, Gernhardt and Reilly assisted space station minutes, Gernhardt and Reilly assisted space station robot arm operator Susan Helms with installation of robot arm operator Susan Helms with installation of robot arm operator Susan Helms with installation of the joint airlock onto the station. the joint airlock onto the station. the joint airlock onto the station. EVA 2, 6 hours, 29 minutes, Gernhardt and Reilly EVA 2, 6 hours, 29 minutes, Gernhardt and Reilly EVA 2, 6 hours, 29 minutes, Gernhardt and Reilly installed three high-pressure gas tanks (two oxygen installed three high-pressure gas tanks (two oxygen installed three high-pressure gas tanks (two oxygen and one nitrogen) onto the joint airlock. EVA 3, 4 and one nitrogen) onto the joint airlock. EVA 3, 4 and one nitrogen) onto the joint airlock. EVA 3, 4 hours, 2 minutes, Gernhardt and Reilly, conducting hours, 2 minutes, Gernhardt and Reilly, conducting hours, 2 minutes, Gernhardt and Reilly, conducting first spacewalk from new joint airlock, installed fourth first spacewalk from new joint airlock, installed fourth first spacewalk from new joint airlock, installed fourth high-pressure gas tank (nitrogen) onto the joint air- high-pressure gas tank (nitrogen) onto the joint air- high-pressure gas tank (nitrogen) onto the joint air- lock, plus handholds and communications cables. lock, plus handholds and communications cables. lock, plus handholds and communications cables.

STS-105 Mission Facts — Discovery — STS-105 Mission Facts — Discovery — STS-105 Mission Facts — Discovery — August 10–22, 2001 August 10–22, 2001 August 10–22, 2001

Commander: Scott J. Horowitz Commander: Scott J. Horowitz Commander: Scott J. Horowitz Pilot: Rick Sturckow Pilot: Rick Sturckow Pilot: Rick Sturckow Mission Specialist: Daniel T. Barry Mission Specialist: Daniel T. Barry Mission Specialist: Daniel T. Barry Mission Specialist: Patrick G. Forrester Mission Specialist: Patrick G. Forrester Mission Specialist: Patrick G. Forrester ISS Crew Member: Frank L. Culbertson Jr.—up only ISS Crew Member: Frank L. Culbertson Jr.—up only ISS Crew Member: Frank L. Culbertson Jr.—up only ISS Crew Member: Vladimir N. Dezhurov, Russian Space ISS Crew Member: Vladimir N. Dezhurov, Russian Space ISS Crew Member: Vladimir N. Dezhurov, Russian Space Agency—up only Agency—up only Agency—up only ISS Crew Member: Mikhail Turin, Russian Space ISS Crew Member: Mikhail Turin, Russian Space ISS Crew Member: Mikhail Turin, Russian Space Agency—up only Agency—up only Agency—up only ISS Crew Member: Yury V. Usachev, Russian Space ISS Crew Member: Yury V. Usachev, Russian Space ISS Crew Member: Yury V. Usachev, Russian Space Agency—down only Agency—down only Agency—down only ISS Crew Member: James S. Voss—down only ISS Crew Member: James S. Voss—down only ISS Crew Member: James S. Voss—down only ISS Crew Member: Susan J. Helms—down only ISS Crew Member: Susan J. Helms—down only ISS Crew Member: Susan J. Helms—down only Mission Duration: 264 hours (11 days), 21 hours, Mission Duration: 264 hours (11 days), 21 hours, Mission Duration: 264 hours (11 days), 21 hours, 13 minutes 13 minutes 13 minutes Miles Traveled: Approximately 4.3 million statute miles Miles Traveled: Approximately 4.3 million statute miles Miles Traveled: Approximately 4.3 million statute miles Inclination: 51.6 degrees Inclination: 51.6 degrees Inclination: 51.6 degrees Orbits of Earth: 186 Orbits of Earth: 186 Orbits of Earth: 186 Orbital Insertion Altitude: 122 nautical miles Orbital Insertion Altitude: 122 nautical miles Orbital Insertion Altitude: 122 nautical miles Orbital ISS Rendezvous Altitude: 240 nautical miles Orbital ISS Rendezvous Altitude: 240 nautical miles Orbital ISS Rendezvous Altitude: 240 nautical miles Lift-Off Weight: 4,518,170 pounds Lift-Off Weight: 4,518,170 pounds Lift-Off Weight: 4,518,170 pounds Orbiter Weight at Lift-Off: 262,477 pounds Orbiter Weight at Lift-Off: 262,477 pounds Orbiter Weight at Lift-Off: 262,477 pounds Payload Weight Up: 29,305 pounds Payload Weight Up: 29,305 pounds Payload Weight Up: 29,305 pounds Landing Touchdown: Approximately 1,595 feet beyond Landing Touchdown: Approximately 1,595 feet beyond Landing Touchdown: Approximately 1,595 feet beyond threshold threshold threshold Landing Rollout: Approximately 10,048 feet Landing Rollout: Approximately 10,048 feet Landing Rollout: Approximately 10,048 feet Landing Speed at Main Gear Touchdown: Approximately Landing Speed at Main Gear Touchdown: Approximately Landing Speed at Main Gear Touchdown: Approximately 202 knots (232 miles per hour) 202 knots (232 miles per hour) 202 knots (232 miles per hour)

Y-89 Y-89 Y-89 STS-105 Mission Facts (Cont) STS-105 Mission Facts (Cont) STS-105 Mission Facts (Cont) Orbiter Weight at Landing: 222,250 pounds Orbiter Weight at Landing: 222,250 pounds Orbiter Weight at Landing: 222,250 pounds Payload Weight Down: 23,456 pounds Payload Weight Down: 23,456 pounds Payload Weight Down: 23,456 pounds Landed: Concrete runway 15 at Kennedy Space Center, Landed: Concrete runway 15 at Kennedy Space Center, Landed: Concrete runway 15 at Kennedy Space Center, Fla. Fla. Fla. Payload: ISS Assembly Flight 7A.1; Leonardo Multi- Payload: ISS Assembly Flight 7A.1; Leonardo Multi- Payload: ISS Assembly Flight 7A.1; Leonardo Multi- Purpose Logistics Module (MPLM); second ISS Purpose Logistics Module (MPLM); second ISS Purpose Logistics Module (MPLM); second ISS crew exchange crew exchange crew exchange Extravehicular Activity (EVAs) conducted by Daniel Barry Extravehicular Activity (EVAs) conducted by Daniel Barry Extravehicular Activity (EVAs) conducted by Daniel Barry and Patrick Forrester. EVA 1, 6 hours, 16 minutes, and Patrick Forrester. EVA 1, 6 hours, 16 minutes, and Patrick Forrester. EVA 1, 6 hours, 16 minutes, Barry and Forrester installed an early ammonia Barry and Forrester installed an early ammonia Barry and Forrester installed an early ammonia servicer onto the P6 truss and installed the Materials servicer onto the P6 truss and installed the Materials servicer onto the P6 truss and installed the Materials International Space Station Experiment onto the International Space Station Experiment onto the International Space Station Experiment onto the joint airlock. EVA 2, 5 hours, 29 minutes, Barry and joint airlock. EVA 2, 5 hours, 29 minutes, Barry and joint airlock. EVA 2, 5 hours, 29 minutes, Barry and Forrester installed handrails and heater cables onto Forrester installed handrails and heater cables onto Forrester installed handrails and heater cables onto the U.S. Laboratory. The cables may be used on the U.S. Laboratory. The cables may be used on the U.S. Laboratory. The cables may be used on mission STS-110 to power heaters on the S0 truss mission STS-110 to power heaters on the S0 truss mission STS-110 to power heaters on the S0 truss segment. segment. segment.

STS-108 Mission Facts — Endeavour — STS-108 Mission Facts — Endeavour — STS-108 Mission Facts — Endeavour — December 5–17, 2001 December 5–17, 2001 December 5–17, 2001

Commander: Dominic L. Gorie Commander: Dominic L. Gorie Commander: Dominic L. Gorie Pilot: Mark E. Kelly Pilot: Mark E. Kelly Pilot: Mark E. Kelly Mission Specialist: Linda M. Godwin Mission Specialist: Linda M. Godwin Mission Specialist: Linda M. Godwin Mission Specialist: Daniel M. Tani Mission Specialist: Daniel M. Tani Mission Specialist: Daniel M. Tani ISS Crew Member: Yuri I. Onufrienko, Russian Space ISS Crew Member: Yuri I. Onufrienko, Russian Space ISS Crew Member: Yuri I. Onufrienko, Russian Space Agency—up only Agency—up only Agency—up only ISS Crew Member: Daniel W. Bursch—up only ISS Crew Member: Daniel W. Bursch—up only ISS Crew Member: Daniel W. Bursch—up only ISS Crew Member: Carl E. Walz—up only ISS Crew Member: Carl E. Walz—up only ISS Crew Member: Carl E. Walz—up only ISS Crew Member: Frank L. Culbertson—down only ISS Crew Member: Frank L. Culbertson—down only ISS Crew Member: Frank L. Culbertson—down only ISS Crew Member: Vladimir N. Dezhurov, Russian ISS Crew Member: Vladimir N. Dezhurov, Russian ISS Crew Member: Vladimir N. Dezhurov, Russian Space Agency—down only Space Agency—down only Space Agency—down only ISS Crew Member: Mikhail Turin, Russian Space ISS Crew Member: Mikhail Turin, Russian Space ISS Crew Member: Mikhail Turin, Russian Space Agency—down only Agency—down only Agency—down only Mission Duration: 264 hours (11 days), 19 hours, Mission Duration: 264 hours (11 days), 19 hours, Mission Duration: 264 hours (11 days), 19 hours, 37 minutes 37 minutes 37 minutes Miles Traveled: Approximately 4.8 million statute miles Miles Traveled: Approximately 4.8 million statute miles Miles Traveled: Approximately 4.8 million statute miles Orbits of Earth: 185 Orbits of Earth: 185 Orbits of Earth: 185 Orbital Insertion Altitude: 122 nautical miles Orbital Insertion Altitude: 122 nautical miles Orbital Insertion Altitude: 122 nautical miles Inclination: 51.6 degrees Inclination: 51.6 degrees Inclination: 51.6 degrees Orbital ISS Rendezvous Altitude: 205 nautical miles Orbital ISS Rendezvous Altitude: 205 nautical miles Orbital ISS Rendezvous Altitude: 205 nautical miles Lift-off Weight: 4,519,872 pounds Lift-off Weight: 4,519,872 pounds Lift-off Weight: 4,519,872 pounds Payload Weight Up: 31,393 pounds Payload Weight Up: 31,393 pounds Payload Weight Up: 31,393 pounds Orbiter Weight at Landing: 225,169 pounds Orbiter Weight at Landing: 225,169 pounds Orbiter Weight at Landing: 225,169 pounds Payload Weight Down: 28,826 pounds Payload Weight Down: 28,826 pounds Payload Weight Down: 28,826 pounds Landed: Concrete runway 15 at Kennedy Space Center, Landed: Concrete runway 15 at Kennedy Space Center, Landed: Concrete runway 15 at Kennedy Space Center, Fla. Fla. Fla. Payload: ISS Assembly Flight UF-1; Raffaello Multi- Payload: ISS Assembly Flight UF-1; Raffaello Multi- Payload: ISS Assembly Flight UF-1; Raffaello Multi- Purpose Logistics Module, Multiple Application Purpose Logistics Module, Multiple Application Purpose Logistics Module, Multiple Application Customized Hitchhiker-1, STARSHINE 2, “Flags Customized Hitchhiker-1, STARSHINE 2, “Flags Customized Hitchhiker-1, STARSHINE 2, “Flags for Heroes and Families” in honor of the victims of for Heroes and Families” in honor of the victims of for Heroes and Families” in honor of the victims of 9-11-01; third ISS crew exchange 9-11-01; third ISS crew exchange 9-11-01; third ISS crew exchange

Y-90 Y-90 Y-90 STS-108 Mission Facts (Cont) STS-108 Mission Facts (Cont) STS-108 Mission Facts (Cont) Extravehicular Activity (EVA) conducted by Linda God- Extravehicular Activity (EVA) conducted by Linda God- Extravehicular Activity (EVA) conducted by Linda God- win and Daniel Tani; 4 hours, 12 minutes; Godwin win and Daniel Tani; 4 hours, 12 minutes; Godwin win and Daniel Tani; 4 hours, 12 minutes; Godwin and Tani installed insulation on mechanisms that and Tani installed insulation on mechanisms that and Tani installed insulation on mechanisms that rotate the International Space Station’s main solar rotate the International Space Station’s main solar rotate the International Space Station’s main solar arrays. This completed a record year for space- arrays. This completed a record year for space- arrays. This completed a record year for space- walks, with 12 spacewalks originating from the walks, with 12 spacewalks originating from the walks, with 12 spacewalks originating from the space shuttle and six from the space station. space shuttle and six from the space station. space shuttle and six from the space station.

STS-109 Mission Facts — Columbia — STS-109 Mission Facts — Columbia — STS-109 Mission Facts — Columbia — March 1–12, 2002 March 1–12, 2002 March 1–12, 2002

Commander: Scott D. Altman Commander: Scott D. Altman Commander: Scott D. Altman Pilot: Duane G. Carey Pilot: Duane G. Carey Pilot: Duane G. Carey Payload Commander: John M. Grunsfeld Payload Commander: John M. Grunsfeld Payload Commander: John M. Grunsfeld Mission Specialist: Nancy J. Currie Mission Specialist: Nancy J. Currie Mission Specialist: Nancy J. Currie Mission Specialist: James H. Newman Mission Specialist: James H. Newman Mission Specialist: James H. Newman Mission Specialist: Richard M. Linnehan Mission Specialist: Richard M. Linnehan Mission Specialist: Richard M. Linnehan Mission Specialist: Michael J. Massimino Mission Specialist: Michael J. Massimino Mission Specialist: Michael J. Massimino Mission Duration: 240 hours (10 days), 22 hours, Mission Duration: 240 hours (10 days), 22 hours, Mission Duration: 240 hours (10 days), 22 hours, 11 minutes 11 minutes 11 minutes Miles Traveled: Approximately 3.9 million statute miles Miles Traveled: Approximately 3.9 million statute miles Miles Traveled: Approximately 3.9 million statute miles Orbits of Earth: 165 Orbits of Earth: 165 Orbits of Earth: 165 Inclination: 28.5 degrees Inclination: 28.5 degrees Inclination: 28.5 degrees Orbital Altitude: 308 nautical miles Orbital Altitude: 308 nautical miles Orbital Altitude: 308 nautical miles Lift-Off Weight: 4,515,646 pounds Lift-Off Weight: 4,515,646 pounds Lift-Off Weight: 4,515,646 pounds Orbiter Weight at Lift-Off: 260,665 pounds Orbiter Weight at Lift-Off: 260,665 pounds Orbiter Weight at Lift-Off: 260,665 pounds Payload Weight Up: 27,594 pounds Payload Weight Up: 27,594 pounds Payload Weight Up: 27,594 pounds Orbiter Weight at Landing: 258,788 pounds Orbiter Weight at Landing: 258,788 pounds Orbiter Weight at Landing: 258,788 pounds Payload Weight Down: 25,717 pounds Payload Weight Down: 25,717 pounds Payload Weight Down: 25,717 pounds Landed: Concrete runway 33 at Kennedy Space Center, Landed: Concrete runway 33 at Kennedy Space Center, Landed: Concrete runway 33 at Kennedy Space Center, Fla. Fla. Fla. Payload: Hubble Space Telescope Servicing Mission Payload: Hubble Space Telescope Servicing Mission Payload: Hubble Space Telescope Servicing Mission 3B; Advanced Camera for Surveys, new rigid solar 3B; Advanced Camera for Surveys, new rigid solar 3B; Advanced Camera for Surveys, new rigid solar arrays (SA3), new power control unit (PCU), new arrays (SA3), new power control unit (PCU), new arrays (SA3), new power control unit (PCU), new cryocooler for Near-Infrared Camera and Multi- cryocooler for Near-Infrared Camera and Multi- cryocooler for Near-Infrared Camera and Multi- Object Spectrometer (NICMOS), reaction wheel Object Spectrometer (NICMOS), reaction wheel Object Spectrometer (NICMOS), reaction wheel assembly (RWA1) assembly (RWA1) assembly (RWA1) Extravehicular Activity (EVA) conducted by team of John Extravehicular Activity (EVA) conducted by team of John Extravehicular Activity (EVA) conducted by team of John Grunsfeld and Richard Linnehan and team of James Grunsfeld and Richard Linnehan and team of James Grunsfeld and Richard Linnehan and team of James Newman and Michael Massimino. EVA 1, 7 hours, Newman and Michael Massimino. EVA 1, 7 hours, Newman and Michael Massimino. EVA 1, 7 hours, 1 minute, Grunsfeld and Linnehan replaced the 1 minute, Grunsfeld and Linnehan replaced the 1 minute, Grunsfeld and Linnehan replaced the starboard solar array; EVA 2, 7 hours, 16 minutes, starboard solar array; EVA 2, 7 hours, 16 minutes, starboard solar array; EVA 2, 7 hours, 16 minutes, Newman and Massimino replaced the port solar Newman and Massimino replaced the port solar Newman and Massimino replaced the port solar array and reaction wheel assembly; EVA 3, 6 hours, array and reaction wheel assembly; EVA 3, 6 hours, array and reaction wheel assembly; EVA 3, 6 hours, 48 minutes, Grunsfeld and Linnehan replaced the 48 minutes, Grunsfeld and Linnehan replaced the 48 minutes, Grunsfeld and Linnehan replaced the power control unit; EVA 4, 7 hours, 30 minutes, power control unit; EVA 4, 7 hours, 30 minutes, power control unit; EVA 4, 7 hours, 30 minutes, Newman and Massimino replaced the Faint Object Newman and Massimino replaced the Faint Object Newman and Massimino replaced the Faint Object Camera with the Advanced Camera for Surveys; Camera with the Advanced Camera for Surveys; Camera with the Advanced Camera for Surveys; EVA 5, 7 hours, 20 minutes, Grunsfeld and Linnehan EVA 5, 7 hours, 20 minutes, Grunsfeld and Linnehan EVA 5, 7 hours, 20 minutes, Grunsfeld and Linnehan installed a new cooling system for the Near-Infrared installed a new cooling system for the Near-Infrared installed a new cooling system for the Near-Infrared Camera and Multi-Object Spectrometer. Camera and Multi-Object Spectrometer. Camera and Multi-Object Spectrometer.

Y-91 Y-91 Y-91 STS-110 Mission Facts — Atlantis — STS-110 Mission Facts — Atlantis — STS-110 Mission Facts — Atlantis — April 8–19, 2002 April 8–19, 2002 April 8–19, 2002 Commander: Michael J. Bloomfield Commander: Michael J. Bloomfield Commander: Michael J. Bloomfield Pilot: Stephen N. Frick Pilot: Stephen N. Frick Pilot: Stephen N. Frick Mission Specialist: Jerry L. Ross Mission Specialist: Jerry L. Ross Mission Specialist: Jerry L. Ross Mission Specialist: Steven L. Smith Mission Specialist: Steven L. Smith Mission Specialist: Steven L. Smith Mission Specialist: Ellen Ochoa Mission Specialist: Ellen Ochoa Mission Specialist: Ellen Ochoa Mission Specialist: Lee M.E. Morin Mission Specialist: Lee M.E. Morin Mission Specialist: Lee M.E. Morin Mission Specialist: Rex J. Walheim Mission Specialist: Rex J. Walheim Mission Specialist: Rex J. Walheim Mission Duration: 240 hours (10 days), 19 hours, Mission Duration: 240 hours (10 days), 19 hours, Mission Duration: 240 hours (10 days), 19 hours, 42 minutes 42 minutes 42 minutes Miles Traveled: Approximately 4.5 million statute miles Miles Traveled: Approximately 4.5 million statute miles Miles Traveled: Approximately 4.5 million statute miles Orbits of Earth: 171 Orbits of Earth: 171 Orbits of Earth: 171 Inclination: 51.6 degrees Inclination: 51.6 degrees Inclination: 51.6 degrees Orbital Altitude: 247 nautical miles Orbital Altitude: 247 nautical miles Orbital Altitude: 247 nautical miles Lift-Off Weight: 4,520,940 pounds Lift-Off Weight: 4,520,940 pounds Lift-Off Weight: 4,520,940 pounds Orbiter Weight at Lift-Off: 257,079 pounds Orbiter Weight at Lift-Off: 257,079 pounds Orbiter Weight at Lift-Off: 257,079 pounds Payload Weight Up: 28,379 pounds Payload Weight Up: 28,379 pounds Payload Weight Up: 28,379 pounds Orbiter Weight at Landing: 200,657 pounds Orbiter Weight at Landing: 200,657 pounds Orbiter Weight at Landing: 200,657 pounds Payload Weight Down: 1,493 pounds Payload Weight Down: 1,493 pounds Payload Weight Down: 1,493 pounds Landed: Concrete runway 33 at Kennedy Space Center, Landed: Concrete runway 33 at Kennedy Space Center, Landed: Concrete runway 33 at Kennedy Space Center, Fla. Fla. Fla. Payload: ISS Assembly Flight 8A; Starboard-zero (S0) Payload: ISS Assembly Flight 8A; Starboard-zero (S0) Payload: ISS Assembly Flight 8A; Starboard-zero (S0) Central Integrated Truss Structure; Mobile Trans- Central Integrated Truss Structure; Mobile Trans- Central Integrated Truss Structure; Mobile Trans- porter, which will be attached to the Mobile Base porter, which will be attached to the Mobile Base porter, which will be attached to the Mobile Base System during STS-111 to create the first “railroad in System during STS-111 to create the first “railroad in System during STS-111 to create the first “railroad in space”; first flight of three Block II main engines space”; first flight of three Block II main engines space”; first flight of three Block II main engines Extravehicular Activity (EVA) conducted by team of Extravehicular Activity (EVA) conducted by team of Extravehicular Activity (EVA) conducted by team of Steven Smith and Rex Walheim and team of Jerry Steven Smith and Rex Walheim and team of Jerry Steven Smith and Rex Walheim and team of Jerry Ross and Lee Morin. EVA 1, 7 hours, 48 minutes; Ross and Lee Morin. EVA 1, 7 hours, 48 minutes; Ross and Lee Morin. EVA 1, 7 hours, 48 minutes; after the S0 Truss was lifted by the Canadarm2 from after the S0 Truss was lifted by the Canadarm2 from after the S0 Truss was lifted by the Canadarm2 from Atlantis’ cargo bay and installed on the U.S. Labora- Atlantis’ cargo bay and installed on the U.S. Labora- Atlantis’ cargo bay and installed on the U.S. Labora- tory, Smith and Walheim made power and data tory, Smith and Walheim made power and data tory, Smith and Walheim made power and data connections and bolted two forward struts. EVA 2, 7 connections and bolted two forward struts. EVA 2, 7 connections and bolted two forward struts. EVA 2, 7 hours, 30 minutes; Ross and Morin continued power hours, 30 minutes; Ross and Morin continued power hours, 30 minutes; Ross and Morin continued power and data connections between the S0 and ISS and and data connections between the S0 and ISS and and data connections between the S0 and ISS and bolted two aft struts. EVA 3, 6 hours, 27 minutes; bolted two aft struts. EVA 3, 6 hours, 27 minutes; bolted two aft struts. EVA 3, 6 hours, 27 minutes; Smith and Walheim installed power connections Smith and Walheim installed power connections Smith and Walheim installed power connections for Canadarm2 to use when on the truss. EVA 4, 6 for Canadarm2 to use when on the truss. EVA 4, 6 for Canadarm2 to use when on the truss. EVA 4, 6 hours, 25 minutes; Ross and Morin installed a beam hours, 25 minutes; Ross and Morin installed a beam hours, 25 minutes; Ross and Morin installed a beam called the Airlock Spur between the Quest airlock called the Airlock Spur between the Quest airlock called the Airlock Spur between the Quest airlock and the S0 and installed handrails on the S0. Ross and the S0 and installed handrails on the S0. Ross and the S0 and installed handrails on the S0. Ross set new record for most spacewalks (nine), as well set new record for most spacewalks (nine), as well set new record for most spacewalks (nine), as well as a new record for most space shuttle missions as a new record for most space shuttle missions as a new record for most space shuttle missions (seven). (seven). (seven).

Y-92 Y-92 Y-92 STS-111 Mission Facts — Endeavour — STS-111 Mission Facts — Endeavour — STS-111 Mission Facts — Endeavour — June 5–19, 2002 June 5–19, 2002 June 5–19, 2002 Commander: Kenneth D. Cockrell Commander: Kenneth D. Cockrell Commander: Kenneth D. Cockrell Pilot: Paul S. Lockhart Pilot: Paul S. Lockhart Pilot: Paul S. Lockhart Mission Specialist: Franklin R. Chang-Diaz Mission Specialist: Franklin R. Chang-Diaz Mission Specialist: Franklin R. Chang-Diaz Mission Specialist: Philippe Perrin, Centre National Mission Specialist: Philippe Perrin, Centre National Mission Specialist: Philippe Perrin, Centre National D’Etudes Spatiales (CNES, French Space Agency) D’Etudes Spatiales (CNES, French Space Agency) D’Etudes Spatiales (CNES, French Space Agency) ISS Crew Member: Valery G. Korzun, Russian Space ISS Crew Member: Valery G. Korzun, Russian Space ISS Crew Member: Valery G. Korzun, Russian Space Agency—up only Agency—up only Agency—up only ISS Crew Member: Peggy A. Whitson—up only ISS Crew Member: Peggy A. Whitson—up only ISS Crew Member: Peggy A. Whitson—up only ISS Crew Member: Sergei Y. Treschev, Russian Space ISS Crew Member: Sergei Y. Treschev, Russian Space ISS Crew Member: Sergei Y. Treschev, Russian Space Agency—up only Agency—up only Agency—up only ISS Crew Member: Yuri I. Onufrienko, Russian Space ISS Crew Member: Yuri I. Onufrienko, Russian Space ISS Crew Member: Yuri I. Onufrienko, Russian Space Agency—down only Agency—down only Agency—down only ISS Crew Member: Carl E. Walz—down only ISS Crew Member: Carl E. Walz—down only ISS Crew Member: Carl E. Walz—down only ISS Crew Member: Daniel W. Bursch—down only ISS Crew Member: Daniel W. Bursch—down only ISS Crew Member: Daniel W. Bursch—down only Mission Duration: 312 hours (13 days), 20 hours, Mission Duration: 312 hours (13 days), 20 hours, Mission Duration: 312 hours (13 days), 20 hours, 35 minutes 35 minutes 35 minutes Miles Traveled: Approximately 5.78 million statute miles Miles Traveled: Approximately 5.78 million statute miles Miles Traveled: Approximately 5.78 million statute miles Orbits of Earth: 217 Orbits of Earth: 217 Orbits of Earth: 217 Inclination: 51.6 degrees Inclination: 51.6 degrees Inclination: 51.6 degrees Orbital ISS Altitude: Approximately 240 nautical miles Orbital ISS Altitude: Approximately 240 nautical miles Orbital ISS Altitude: Approximately 240 nautical miles Lift-Off Weight: 4,518,239 pounds Lift-Off Weight: 4,518,239 pounds Lift-Off Weight: 4,518,239 pounds Orbiter Weight at Lift-Off: 256,884 pounds Orbiter Weight at Lift-Off: 256,884 pounds Orbiter Weight at Lift-Off: 256,884 pounds Payload Weight Up: 29,810 pounds Payload Weight Up: 29,810 pounds Payload Weight Up: 29,810 pounds Orbiter Weight at Landing: 219,103 pounds Orbiter Weight at Landing: 219,103 pounds Orbiter Weight at Landing: 219,103 pounds Payload Weight Down: 22,099 pounds Payload Weight Down: 22,099 pounds Payload Weight Down: 22,099 pounds Landed: Concrete runway 22 at Edwards Air Force Base, Landed: Concrete runway 22 at Edwards Air Force Base, Landed: Concrete runway 22 at Edwards Air Force Base, Calif. Calif. Calif. Payload: ISS Utilization Flight UF-2; Leonardo Multi-Pur- Payload: ISS Utilization Flight UF-2; Leonardo Multi-Pur- Payload: ISS Utilization Flight UF-2; Leonardo Multi-Pur- pose Logistics Module carrying experiment racks, pose Logistics Module carrying experiment racks, pose Logistics Module carrying experiment racks, equipment, and supplies; Mobile Base System equipment, and supplies; Mobile Base System equipment, and supplies; Mobile Base System (MBS) installed on Mobile Transporter (MT) to (MBS) installed on Mobile Transporter (MT) to (MBS) installed on Mobile Transporter (MT) to com plete Mobile Servicing System; replacement com plete Mobile Servicing System; replacement com plete Mobile Servicing System; replacement of Canadarm2 wrist roll joint; and fourth ISS crew of Canadarm2 wrist roll joint; and fourth ISS crew of Canadarm2 wrist roll joint; and fourth ISS crew exchange. ISS crew members Walz and Bursch set exchange. ISS crew members Walz and Bursch set exchange. ISS crew members Walz and Bursch set new record for longest U.S. space flight (196 days), new record for longest U.S. space flight (196 days), new record for longest U.S. space flight (196 days), breaking the previous record of 188 days in space breaking the previous record of 188 days in space breaking the previous record of 188 days in space held by Shannon Lucid aboard the Russian space held by Shannon Lucid aboard the Russian space held by Shannon Lucid aboard the Russian space station Mir. Walz now also holds the U.S. record for station Mir. Walz now also holds the U.S. record for station Mir. Walz now also holds the U.S. record for the most cumulative time in space with 231 days. the most cumulative time in space with 231 days. the most cumulative time in space with 231 days. Extravehicular Activity (EVA) conducted by team of Extravehicular Activity (EVA) conducted by team of Extravehicular Activity (EVA) conducted by team of Franklin Chang-Diaz and Philippe Perrin. EVA 1, 7 Franklin Chang-Diaz and Philippe Perrin. EVA 1, 7 Franklin Chang-Diaz and Philippe Perrin. EVA 1, 7 hours, 14 minutes; Chang-Diaz and Perrin attached hours, 14 minutes; Chang-Diaz and Perrin attached hours, 14 minutes; Chang-Diaz and Perrin attached a power and data grapple fixture onto the P6 truss, a power and data grapple fixture onto the P6 truss, a power and data grapple fixture onto the P6 truss, setting the stage for the future relocation of the P6, setting the stage for the future relocation of the P6, setting the stage for the future relocation of the P6, and removed thermal blankets to prepare MBS for and removed thermal blankets to prepare MBS for and removed thermal blankets to prepare MBS for installation. Whitson and Walz used Canadarm2 installation. Whitson and Walz used Canadarm2 installation. Whitson and Walz used Canadarm2 to lift the MBS out of the payload bay. EVA 2, 5 to lift the MBS out of the payload bay. EVA 2, 5 to lift the MBS out of the payload bay. EVA 2, 5 hours; the focus was on outfitting and permanently hours; the focus was on outfitting and permanently hours; the focus was on outfitting and permanently attach ing the MBS to the MT. Chang-Diaz and Perrin attach ing the MBS to the MT. Chang-Diaz and Perrin attach ing the MBS to the MT. Chang-Diaz and Perrin attached power, data, and video cables from the attached power, data, and video cables from the attached power, data, and video cables from the station to the MBS. EVA 3, 7 hours, 17 minutes; station to the MBS. EVA 3, 7 hours, 17 minutes; station to the MBS. EVA 3, 7 hours, 17 minutes; Chang-Diaz and Perrin replaced Canadarm2’s wrist Chang-Diaz and Perrin replaced Canadarm2’s wrist Chang-Diaz and Perrin replaced Canadarm2’s wrist roll joint. roll joint. roll joint.

Y-93 Y-93 Y-93 STS-112 Mission Facts — Atlantis — STS-112 Mission Facts — Atlantis — STS-112 Mission Facts — Atlantis — October 7–18, 2002 October 7–18, 2002 October 7–18, 2002 Commander: Jeffrey S. Ashby Commander: Jeffrey S. Ashby Commander: Jeffrey S. Ashby Pilot: Pamela A. Melroy Pilot: Pamela A. Melroy Pilot: Pamela A. Melroy Mission Specialist: David A. Wolf Mission Specialist: David A. Wolf Mission Specialist: David A. Wolf Mission Specialist: Piers J. Sellers Mission Specialist: Piers J. Sellers Mission Specialist: Piers J. Sellers Mission Specialist: Sandra H. Magnus Mission Specialist: Sandra H. Magnus Mission Specialist: Sandra H. Magnus Mission Specialist: Fyodor N. Yurchikhin, Russian Space Mission Specialist: Fyodor N. Yurchikhin, Russian Space Mission Specialist: Fyodor N. Yurchikhin, Russian Space Agency Agency Agency Launched: 3:45:51 p.m. EDT, launch pad 39B, Kennedy Launched: 3:45:51 p.m. EDT, launch pad 39B, Kennedy Launched: 3:45:51 p.m. EDT, launch pad 39B, Kennedy Space Center, Fla. Space Center, Fla. Space Center, Fla. Mission Duration: 240 hours (10 days), 19 hours, Mission Duration: 240 hours (10 days), 19 hours, Mission Duration: 240 hours (10 days), 19 hours, 58 minutes 58 minutes 58 minutes Miles Traveled: Approximately 4.5 million statute miles Miles Traveled: Approximately 4.5 million statute miles Miles Traveled: Approximately 4.5 million statute miles Orbits of Earth: 170 Orbits of Earth: 170 Orbits of Earth: 170 Inclination: 51.6 degrees Inclination: 51.6 degrees Inclination: 51.6 degrees Orbital Altitude: 210 nautical miles Orbital Altitude: 210 nautical miles Orbital Altitude: 210 nautical miles Lift-Off Weight: 4,521,314 pounds Lift-Off Weight: 4,521,314 pounds Lift-Off Weight: 4,521,314 pounds Orbiter Weight at Lift-Off: 265,812 pounds Orbiter Weight at Lift-Off: 265,812 pounds Orbiter Weight at Lift-Off: 265,812 pounds Payload Weight Up: 29,502 pounds Payload Weight Up: 29,502 pounds Payload Weight Up: 29,502 pounds Orbiter Weight at Landing: 201,299 pounds Orbiter Weight at Landing: 201,299 pounds Orbiter Weight at Landing: 201,299 pounds Payload Weight Down: 1,733 pounds Payload Weight Down: 1,733 pounds Payload Weight Down: 1,733 pounds Landed: 11:44:35 a.m. EDT, concrete runway 33, Landed: 11:44:35 a.m. EDT, concrete runway 33, Landed: 11:44:35 a.m. EDT, concrete runway 33, Kennedy Space Center, Fla. Kennedy Space Center, Fla. Kennedy Space Center, Fla. Payload: ISS Assembly Flight 9A; 14-ton Starboard-One Payload: ISS Assembly Flight 9A; 14-ton Starboard-One Payload: ISS Assembly Flight 9A; 14-ton Starboard-One (S1) Truss Structure preintegrated with a standard (S1) Truss Structure preintegrated with a standard (S1) Truss Structure preintegrated with a standard Tracking and Data Relay Satellite Sys tem (TDRSS) Tracking and Data Relay Satellite Sys tem (TDRSS) Tracking and Data Relay Satellite Sys tem (TDRSS) transponder, Audio Communication System (ACS) transponder, Audio Communication System (ACS) transponder, Audio Communication System (ACS) baseband signal processor, S-band communication baseband signal processor, S-band communication baseband signal processor, S-band communication equipment, Thermal Radiator Rotary Joint (TRRJ), equipment, Thermal Radiator Rotary Joint (TRRJ), equipment, Thermal Radiator Rotary Joint (TRRJ), three External Active Thermal Control System three External Active Thermal Control System three External Active Thermal Control System (EATCS) radiators, Direct Current (DC)-to-DC (EATCS) radiators, Direct Current (DC)-to-DC (EATCS) radiators, Direct Current (DC)-to-DC Converter Unit (DDCU), Remote Power Controller Converter Unit (DDCU), Remote Power Controller Converter Unit (DDCU), Remote Power Controller Module (RPCM), and Crew Equipment Translation Module (RPCM), and Crew Equipment Translation Module (RPCM), and Crew Equipment Translation Aid (CETA) cart; secondary payloads of Spatial Het- Aid (CETA) cart; secondary payloads of Spatial Het- Aid (CETA) cart; secondary payloads of Spatial Het- erodyne Imager for Mesospheric Radicals (SHIM- erodyne Imager for Mesospheric Radicals (SHIM- erodyne Imager for Mesospheric Radicals (SHIM- MER) and Ram Burn Observation (RAMBO); three MER) and Ram Burn Observation (RAMBO); three MER) and Ram Burn Observation (RAMBO); three DTOs; eight DSOs; first use of Shuttle Observation DTOs; eight DSOs; first use of Shuttle Observation DTOs; eight DSOs; first use of Shuttle Observation Camera System mounted to external tank Camera System mounted to external tank Camera System mounted to external tank Extravehicular Activity (EVA) conducted by team of Extravehicular Activity (EVA) conducted by team of Extravehicular Activity (EVA) conducted by team of David Wolf and Piers Sellers from joint airlock David Wolf and Piers Sellers from joint airlock David Wolf and Piers Sellers from joint airlock “Quest.” EVA 1, 7 hours, 1 minute; after the S1 Truss “Quest.” EVA 1, 7 hours, 1 minute; after the S1 Truss “Quest.” EVA 1, 7 hours, 1 minute; after the S1 Truss was lifted from Atlantis’ cargo bay by the was lifted from Atlantis’ cargo bay by the was lifted from Atlantis’ cargo bay by the Canadarm2, operated by ISS crew member Peggy Canadarm2, operated by ISS crew member Peggy Canadarm2, operated by ISS crew member Peggy Whitson, and attached to the S0 Truss, Wolf and Whitson, and attached to the S0 Truss, Wolf and Whitson, and attached to the S0 Truss, Wolf and Sellers attached power, data, and fluid lines between Sellers attached power, data, and fluid lines between Sellers attached power, data, and fluid lines between the S1 and S0, deployed the station’s second S- the S1 and S0, deployed the station’s second S- the S1 and S0, deployed the station’s second S- band communications system, and installed the first band communications system, and installed the first band communications system, and installed the first of two external camera systems. EVA 2, 6 hours, 4 of two external camera systems. EVA 2, 6 hours, 4 of two external camera systems. EVA 2, 6 hours, 4 minutes; Wolf and Sellers set up a second camera minutes; Wolf and Sellers set up a second camera minutes; Wolf and Sellers set up a second camera

Y-94 Y-94 Y-94 STS-112 Mission Facts (Cont) STS-112 Mission Facts (Cont) STS-112 Mission Facts (Cont)

system, released restraints on the CETA cart, and system, released restraints on the CETA cart, and system, released restraints on the CETA cart, and attached ammonia tank assembly cables. EVA 3, 6 attached ammonia tank assembly cables. EVA 3, 6 attached ammonia tank assembly cables. EVA 3, 6 hours, 36 minutes; Wolf and Sellers removed and hours, 36 minutes; Wolf and Sellers removed and hours, 36 minutes; Wolf and Sellers removed and replaced the Interface Umbilical Assembly on the replaced the Interface Umbilical Assembly on the replaced the Interface Umbilical Assembly on the station’s Mobile Transporter and installed jumpers station’s Mobile Transporter and installed jumpers station’s Mobile Transporter and installed jumpers and spool positioning devices on the ammonia lines and spool positioning devices on the ammonia lines and spool positioning devices on the ammonia lines between the S1 and S0 Trusses. between the S1 and S0 Trusses. between the S1 and S0 Trusses.

STS-113 Mission Facts — Endeavour — STS-113 Mission Facts — Endeavour — STS-113 Mission Facts — Endeavour — Nov. 23–Dec. 7, 2002 Nov. 23–Dec. 7, 2002 Nov. 23–Dec. 7, 2002

Commander: James D. Wetherbee Commander: James D. Wetherbee Commander: James D. Wetherbee Pilot: Paul S. Lockhart Pilot: Paul S. Lockhart Pilot: Paul S. Lockhart Mission Specialist: Michael E. Lopez-Alegria Mission Specialist: Michael E. Lopez-Alegria Mission Specialist: Michael E. Lopez-Alegria Mission Specialist: John B. Herrington Mission Specialist: John B. Herrington Mission Specialist: John B. Herrington ISS Crew Member: Kenneth D. Bowersox—up only ISS Crew Member: Kenneth D. Bowersox—up only ISS Crew Member: Kenneth D. Bowersox—up only ISS Crew Member: Nikolai M. Budarin, Russian Space ISS Crew Member: Nikolai M. Budarin, Russian Space ISS Crew Member: Nikolai M. Budarin, Russian Space Agency—up only Agency—up only Agency—up only ISS Crew Member: Donald R. Pettit—up only ISS Crew Member: Donald R. Pettit—up only ISS Crew Member: Donald R. Pettit—up only ISS Crew Member: Valeri G. Korzun, Russian Space ISS Crew Member: Valeri G. Korzun, Russian Space ISS Crew Member: Valeri G. Korzun, Russian Space Agency—down only Agency—down only Agency—down only ISS Crew Member: Peggy A. Whitson—down only ISS Crew Member: Peggy A. Whitson—down only ISS Crew Member: Peggy A. Whitson—down only ISS Crew Member: Sergei Y. Treschev, Russian Space ISS Crew Member: Sergei Y. Treschev, Russian Space ISS Crew Member: Sergei Y. Treschev, Russian Space Agency—down only Agency—down only Agency—down only Launched: 7:49:47 p.m. EST, launch pad 39A, Kennedy Launched: 7:49:47 p.m. EST, launch pad 39A, Kennedy Launched: 7:49:47 p.m. EST, launch pad 39A, Kennedy Space Center, Fla. Space Center, Fla. Space Center, Fla. Mission Duration: 312 hours (13 days), 18 hours, Mission Duration: 312 hours (13 days), 18 hours, Mission Duration: 312 hours (13 days), 18 hours, 47 minutes 47 minutes 47 minutes Miles Traveled: Approximately 5.74 million statute miles Miles Traveled: Approximately 5.74 million statute miles Miles Traveled: Approximately 5.74 million statute miles Orbits of Earth: 215 Orbits of Earth: 215 Orbits of Earth: 215 Inclination: 51.6 degrees Inclination: 51.6 degrees Inclination: 51.6 degrees Orbital Altitude: 215 nautical miles Orbital Altitude: 215 nautical miles Orbital Altitude: 215 nautical miles Lift-Off Weight: 4,521,249 pounds Lift-Off Weight: 4,521,249 pounds Lift-Off Weight: 4,521,249 pounds Orbiter Weight at Lift-Off: 265,974 pounds Orbiter Weight at Lift-Off: 265,974 pounds Orbiter Weight at Lift-Off: 265,974 pounds Payload Weight Up: 30,217 pounds Payload Weight Up: 30,217 pounds Payload Weight Up: 30,217 pounds Orbiter Weight at Landing: 201,668 pounds Orbiter Weight at Landing: 201,668 pounds Orbiter Weight at Landing: 201,668 pounds Payload Weight Down: 2,268 pounds Payload Weight Down: 2,268 pounds Payload Weight Down: 2,268 pounds Landed: 2:37:12 p.m. EST, concrete runway 33, Kennedy Landed: 2:37:12 p.m. EST, concrete runway 33, Kennedy Landed: 2:37:12 p.m. EST, concrete runway 33, Kennedy Space Center, Fla. Space Center, Fla. Space Center, Fla. Payload: ISS Assembly Flight 11A; 14-ton Port-One (P1) Payload: ISS Assembly Flight 11A; 14-ton Port-One (P1) Payload: ISS Assembly Flight 11A; 14-ton Port-One (P1) Truss Structure preintegrated with Ultra-high Fre- Truss Structure preintegrated with Ultra-high Fre- Truss Structure preintegrated with Ultra-high Fre- quency (UHF) communication equipment, Thermal quency (UHF) communication equipment, Thermal quency (UHF) communication equipment, Thermal Radiator Rotary Joint (TRRJ), three External Active Radiator Rotary Joint (TRRJ), three External Active Radiator Rotary Joint (TRRJ), three External Active Thermal Control System (EATCS) radiators, Direct Thermal Control System (EATCS) radiators, Direct Thermal Control System (EATCS) radiators, Direct Current (DC)-to-DC Converter Unit (DDCU), Remote Current (DC)-to-DC Converter Unit (DDCU), Remote Current (DC)-to-DC Converter Unit (DDCU), Remote Power Controller Module (RPCM), Nitrogen Tank Power Controller Module (RPCM), Nitrogen Tank Power Controller Module (RPCM), Nitrogen Tank Assembly (NTA), Ammonia Tank Assembly (ATA), Assembly (NTA), Ammonia Tank Assembly (ATA), Assembly (NTA), Ammonia Tank Assembly (ATA), and Pump Module Assembly (PMA); second Crew and Pump Module Assembly (PMA); second Crew and Pump Module Assembly (PMA); second Crew and Equipment Translation Aid (CETA) cart that can and Equipment Translation Aid (CETA) cart that can and Equipment Translation Aid (CETA) cart that can be manually operated along the Mobile Transporter be manually operated along the Mobile Transporter be manually operated along the Mobile Transporter rail line; Micro-Electromechanical System (MEMS)- rail line; Micro-Electromechanical System (MEMS)- rail line; Micro-Electromechanical System (MEMS)- Based Pico Satellite (PICOSAT) Inspector (MEPSI); Based Pico Satellite (PICOSAT) Inspector (MEPSI); Based Pico Satellite (PICOSAT) Inspector (MEPSI); one DTO; eight DSOs; and fifth ISS crew exchange. one DTO; eight DSOs; and fifth ISS crew exchange. one DTO; eight DSOs; and fifth ISS crew exchange.

Y-95 Y-95 Y-95 STS-113 Mission Facts (Cont) STS-113 Mission Facts (Cont) STS-113 Mission Facts (Cont)

Extravehicular Activity (EVA) conducted by team of Extravehicular Activity (EVA) conducted by team of Extravehicular Activity (EVA) conducted by team of Michael Lopez-Alegria and John Herrington from Michael Lopez-Alegria and John Herrington from Michael Lopez-Alegria and John Herrington from joint airlock “Quest.” ISS robot arm operators: joint airlock “Quest.” ISS robot arm operators: joint airlock “Quest.” ISS robot arm operators: Peggy Whitson, Ken Bowersox, and Don Pettit. Peggy Whitson, Ken Bowersox, and Don Pettit. Peggy Whitson, Ken Bowersox, and Don Pettit. Space Shuttle robot arm operator: Jim Wetherbee. Space Shuttle robot arm operator: Jim Wetherbee. Space Shuttle robot arm operator: Jim Wetherbee. EVA 1, 6 hours, 45 minutes; after the P1 was at- EVA 1, 6 hours, 45 minutes; after the P1 was at- EVA 1, 6 hours, 45 minutes; after the P1 was at- tached to the station, Lopez-Alegria and Herrington tached to the station, Lopez-Alegria and Herrington tached to the station, Lopez-Alegria and Herrington started installing connections between the P1 and started installing connections between the P1 and started installing connections between the P1 and the S0 truss. They installed onto the Unity node the the S0 truss. They installed onto the Unity node the the S0 truss. They installed onto the Unity node the wireless video system external transceiver assembly, wireless video system external transceiver assembly, wireless video system external transceiver assembly, which will be used to support spacewalkers’ helmet which will be used to support spacewalkers’ helmet which will be used to support spacewalkers’ helmet cameras. Herrington released launch restraints on cameras. Herrington released launch restraints on cameras. Herrington released launch restraints on the CETA cart. EVA 2, 6 hours, 10 minutes; Lopez- the CETA cart. EVA 2, 6 hours, 10 minutes; Lopez- the CETA cart. EVA 2, 6 hours, 10 minutes; Lopez- Alegria and Herrington installed another wireless Alegria and Herrington installed another wireless Alegria and Herrington installed another wireless video system external transceiver assembly onto video system external transceiver assembly onto video system external transceiver assembly onto the P1 and relocated the CETA cart from the P1 to the P1 and relocated the CETA cart from the P1 to the P1 and relocated the CETA cart from the P1 to the S1 truss, which will allow the mobile transporter the S1 truss, which will allow the mobile transporter the S1 truss, which will allow the mobile transporter to move along the P1 to assist in future assembly to move along the P1 to assist in future assembly to move along the P1 to assist in future assembly missions. EVA 3, 7 hours, 0 minutes; Lopez-Alegria missions. EVA 3, 7 hours, 0 minutes; Lopez-Alegria missions. EVA 3, 7 hours, 0 minutes; Lopez-Alegria and Herrington installed additional Spool Position- and Herrington installed additional Spool Position- and Herrington installed additional Spool Position- ing Devices, reconfigured electrical har nesses, and ing Devices, reconfigured electrical har nesses, and ing Devices, reconfigured electrical har nesses, and attached ammonia tank assembly lines. attached ammonia tank assembly lines. attached ammonia tank assembly lines.

STS-107 Mission Facts — Columbia — STS-107 Mission Facts — Columbia — STS-107 Mission Facts — Columbia — Jan. 16–Feb. 1, 2003 Jan. 16–Feb. 1, 2003 Jan. 16–Feb. 1, 2003

Commander: Rick D. Husband Commander: Rick D. Husband Commander: Rick D. Husband Pilot: William C. McCool Pilot: William C. McCool Pilot: William C. McCool Payload Commander: Michael P. Anderson Payload Commander: Michael P. Anderson Payload Commander: Michael P. Anderson Mission Specialist: Kalpana Chawla Mission Specialist: Kalpana Chawla Mission Specialist: Kalpana Chawla Mission Specialist: David M. Brown Mission Specialist: David M. Brown Mission Specialist: David M. Brown Mission Specialist: Laurel B. Clark Mission Specialist: Laurel B. Clark Mission Specialist: Laurel B. Clark Payload Specialist: Ilan Ramon, Israel Payload Specialist: Ilan Ramon, Israel Payload Specialist: Ilan Ramon, Israel Launched: 10:39:00 a.m. EST, launch pad 39A, Kennedy Launched: 10:39:00 a.m. EST, launch pad 39A, Kennedy Launched: 10:39:00 a.m. EST, launch pad 39A, Kennedy Space Center, Fla. Space Center, Fla. Space Center, Fla. Mission Duration: 360 hours (15 days), 22 hours, Mission Duration: 360 hours (15 days), 22 hours, Mission Duration: 360 hours (15 days), 22 hours, 21 minutes 21 minutes 21 minutes Miles Traveled: Approximately 7.65 million statute miles Miles Traveled: Approximately 7.65 million statute miles Miles Traveled: Approximately 7.65 million statute miles Orbits of Earth: 255 Orbits of Earth: 255 Orbits of Earth: 255 Inclination: 39 degrees Inclination: 39 degrees Inclination: 39 degrees Orbital Altitude: 150 nautical miles Orbital Altitude: 150 nautical miles Orbital Altitude: 150 nautical miles Lift-Off Weight: 4,525,842 pounds Lift-Off Weight: 4,525,842 pounds Lift-Off Weight: 4,525,842 pounds Orbiter Weight at Lift-Off: 265,226 pounds Orbiter Weight at Lift-Off: 265,226 pounds Orbiter Weight at Lift-Off: 265,226 pounds Payload Weight Up: 24,365 pounds Payload Weight Up: 24,365 pounds Payload Weight Up: 24,365 pounds Payload: First flight of SPACEHAB as the SPACEHAB Payload: First flight of SPACEHAB as the SPACEHAB Payload: First flight of SPACEHAB as the SPACEHAB Research Double Module (SHRDM); Fast Reaction Research Double Module (SHRDM); Fast Reaction Research Double Module (SHRDM); Fast Reaction Experiments Enabling Science, Technology, Ap- Experiments Enabling Science, Technology, Ap- Experiments Enabling Science, Technology, Ap- plications and Research (FREESTAR); first Extended plications and Research (FREESTAR); first Extended plications and Research (FREESTAR); first Extended Duration Orbiter (EDO) mission since STS-90. Duration Orbiter (EDO) mission since STS-90. Duration Orbiter (EDO) mission since STS-90. Mission dedicated to research in physical, life, and Mission dedicated to research in physical, life, and Mission dedicated to research in physical, life, and space sciences, conducted in approximately 80 space sciences, conducted in approximately 80 space sciences, conducted in approximately 80 experiments. experiments. experiments. Loss of vehicle and crew during reentry, 9:00 a.m. EST Loss of vehicle and crew during reentry, 9:00 a.m. EST Loss of vehicle and crew during reentry, 9:00 a.m. EST

Y-96 Y-96 Y-96 STS-114 Mission Facts — Discovery — STS-114 Mission Facts — Discovery — STS-114 Mission Facts — Discovery — July 26–Aug. 9, 2005 July 26–Aug. 9, 2005 July 26–Aug. 9, 2005 Commander: Eileen M. Collins Commander: Eileen M. Collins Commander: Eileen M. Collins Pilot: James M. Kelly Pilot: James M. Kelly Pilot: James M. Kelly Mission Specialist: Soichi Noguchi, National Space Mission Specialist: Soichi Noguchi, National Space Mission Specialist: Soichi Noguchi, National Space Development Agency of Japan (JAXA) Development Agency of Japan (JAXA) Development Agency of Japan (JAXA) Mission Specialist: Stephen K. Robinson Mission Specialist: Stephen K. Robinson Mission Specialist: Stephen K. Robinson Mission Specialist: Andrew S.W. Thomas Mission Specialist: Andrew S.W. Thomas Mission Specialist: Andrew S.W. Thomas Mission Specialist: Wendy B. Lawrence Mission Specialist: Wendy B. Lawrence Mission Specialist: Wendy B. Lawrence Mission Specialist: Charles J. Camarda Mission Specialist: Charles J. Camarda Mission Specialist: Charles J. Camarda Launched: 10:39:00 a.m. EDT, launch pad 39B, Kennedy Launched: 10:39:00 a.m. EDT, launch pad 39B, Kennedy Launched: 10:39:00 a.m. EDT, launch pad 39B, Kennedy Space Center, Fla. Space Center, Fla. Space Center, Fla. Mission Duration: 312 hours (13 days), 21 hours, Mission Duration: 312 hours (13 days), 21 hours, Mission Duration: 312 hours (13 days), 21 hours, 33 minutes 33 minutes 33 minutes Miles Traveled: Approximately 5.8 million statute miles Miles Traveled: Approximately 5.8 million statute miles Miles Traveled: Approximately 5.8 million statute miles Orbits of Earth: 219 Orbits of Earth: 219 Orbits of Earth: 219 Inclination: 51.6 degrees Inclination: 51.6 degrees Inclination: 51.6 degrees Orbital Altitude: 122 nautical miles Orbital Altitude: 122 nautical miles Orbital Altitude: 122 nautical miles Orbital ISS Rendezvous Altitude: Approximately Orbital ISS Rendezvous Altitude: Approximately Orbital ISS Rendezvous Altitude: Approximately 240 nautical miles 240 nautical miles 240 nautical miles Lift-Off Weight: 4,522,992 pounds Lift-Off Weight: 4,522,992 pounds Lift-Off Weight: 4,522,992 pounds Orbiter Weight at Lift-Off: 267,825 pounds Orbiter Weight at Lift-Off: 267,825 pounds Orbiter Weight at Lift-Off: 267,825 pounds Payload Weight Up: 24,365 pounds Payload Weight Up: 24,365 pounds Payload Weight Up: 24,365 pounds Orbiter Weight at Landing: 226,885 pounds Orbiter Weight at Landing: 226,885 pounds Orbiter Weight at Landing: 226,885 pounds Payload Weight Down: 19,420 pounds Payload Weight Down: 19,420 pounds Payload Weight Down: 19,420 pounds Landed: 5:12:36 a.m. PDT, concrete runway 22, Edwards Landed: 5:12:36 a.m. PDT, concrete runway 22, Edwards Landed: 5:12:36 a.m. PDT, concrete runway 22, Edwards Air Force Base, Calif. Air Force Base, Calif. Air Force Base, Calif. Payload: ISS Assembly Flight LF1; first of two Return-to- Payload: ISS Assembly Flight LF1; first of two Return-to- Payload: ISS Assembly Flight LF1; first of two Return-to- Flight missions; Raffaello Multi-Purpose Logistics Flight missions; Raffaello Multi-Purpose Logistics Flight missions; Raffaello Multi-Purpose Logistics Module; test of orbiter boom sensor system (OBSS); Module; test of orbiter boom sensor system (OBSS); Module; test of orbiter boom sensor system (OBSS); test and evaluation of thermal protection system test and evaluation of thermal protection system test and evaluation of thermal protection system (TPS) repair techniques; replaced one ISS control (TPS) repair techniques; replaced one ISS control (TPS) repair techniques; replaced one ISS control gyroscope and restored power to a second gyro- gyroscope and restored power to a second gyro- gyroscope and restored power to a second gyro- scope; installed External Stowage Platform 2 on ISS scope; installed External Stowage Platform 2 on ISS scope; installed External Stowage Platform 2 on ISS for future construction for future construction for future construction Highlight: Before docking with the ISS, Collins performed Highlight: Before docking with the ISS, Collins performed Highlight: Before docking with the ISS, Collins performed the first Rendezvous Pitch Maneuver approximately the first Rendezvous Pitch Maneuver approximately the first Rendezvous Pitch Maneuver approximately 600 feet below the station. The motion flipped the 600 feet below the station. The motion flipped the 600 feet below the station. The motion flipped the shuttle end over end at 3/4 degree per second, shuttle end over end at 3/4 degree per second, shuttle end over end at 3/4 degree per second, allowing ISS crew members to photograph the allowing ISS crew members to photograph the allowing ISS crew members to photograph the underside of Discovery and its heat-resistant tiles in underside of Discovery and its heat-resistant tiles in underside of Discovery and its heat-resistant tiles in detail. detail. detail.

Y-97 Y-97 Y-97 STS-114 Mission Facts (Cont) STS-114 Mission Facts (Cont) STS-114 Mission Facts (Cont) Extravehicular Activity (EVA) conducted by team of Extravehicular Activity (EVA) conducted by team of Extravehicular Activity (EVA) conducted by team of Stephen Robinson and Soichi Noguchi. EVA 1, Stephen Robinson and Soichi Noguchi. EVA 1, Stephen Robinson and Soichi Noguchi. EVA 1, 6 hours, 50 minutes; Robinson and Noguchi worked 6 hours, 50 minutes; Robinson and Noguchi worked 6 hours, 50 minutes; Robinson and Noguchi worked in Discovery’s cargo bay with tiles and reinforced in Discovery’s cargo bay with tiles and reinforced in Discovery’s cargo bay with tiles and reinforced carbon-carbon intentionally damaged on the ground carbon-carbon intentionally damaged on the ground carbon-carbon intentionally damaged on the ground and brought into space to conduct tile repair and and brought into space to conduct tile repair and and brought into space to conduct tile repair and adhesive experiments. In addition, they installed adhesive experiments. In addition, they installed adhesive experiments. In addition, they installed a base and cabling for a stowage platform and a base and cabling for a stowage platform and a base and cabling for a stowage platform and rerouted power to Control Moment Gyroscope 2. rerouted power to Control Moment Gyroscope 2. rerouted power to Control Moment Gyroscope 2. EVA 2, 7 hours, 14 minutes; Robinson and Noguchi EVA 2, 7 hours, 14 minutes; Robinson and Noguchi EVA 2, 7 hours, 14 minutes; Robinson and Noguchi removed the failed Control Moment Gyroscope removed the failed Control Moment Gyroscope removed the failed Control Moment Gyroscope 1 and installed its replacement. EVA 3, 6 hours, 1 and installed its replacement. EVA 3, 6 hours, 1 and installed its replacement. EVA 3, 6 hours, 1 minute; Attached to Canadarm2, Robinson was 1 minute; Attached to Canadarm2, Robinson was 1 minute; Attached to Canadarm2, Robinson was moved to Discovery’s underside, where he pulled moved to Discovery’s underside, where he pulled moved to Discovery’s underside, where he pulled two protruding gap fillers from between thermal pro- two protruding gap fillers from between thermal pro- two protruding gap fillers from between thermal pro- tection tiles. Robinson and Noguchi also installed tection tiles. Robinson and Noguchi also installed tection tiles. Robinson and Noguchi also installed an external stowage platform outside the ISS Quest an external stowage platform outside the ISS Quest an external stowage platform outside the ISS Quest airlock to house spare parts, and Noguchi installed airlock to house spare parts, and Noguchi installed airlock to house spare parts, and Noguchi installed a fifth Materials International Space Station Experi- a fifth Materials International Space Station Experi- a fifth Materials International Space Station Experi- ment (MISSE). ment (MISSE). ment (MISSE).

STS-121 Mission Facts — Discovery — STS-121 Mission Facts — Discovery — STS-121 Mission Facts — Discovery — July 4–17, 2006 July 4–17, 2006 July 4–17, 2006

Commander: Steven W. Lindsey Commander: Steven W. Lindsey Commander: Steven W. Lindsey Pilot: Mark E. Kelly Pilot: Mark E. Kelly Pilot: Mark E. Kelly Mission Specialist: Piers J. Sellers Mission Specialist: Piers J. Sellers Mission Specialist: Piers J. Sellers Mission Specialist: Michael E. Fossum Mission Specialist: Michael E. Fossum Mission Specialist: Michael E. Fossum Mission Specialist: Lisa M. Nowak Mission Specialist: Lisa M. Nowak Mission Specialist: Lisa M. Nowak Mission Specialist: Stephanie D. Wilson Mission Specialist: Stephanie D. Wilson Mission Specialist: Stephanie D. Wilson ISS Crew Member: Thomas Reiter, European Space ISS Crew Member: Thomas Reiter, European Space ISS Crew Member: Thomas Reiter, European Space Agency—up only Agency—up only Agency—up only Launched: 2:38 p.m. EDT, launch pad 39B, Kennedy Launched: 2:38 p.m. EDT, launch pad 39B, Kennedy Launched: 2:38 p.m. EDT, launch pad 39B, Kennedy Space Center, Fla. Space Center, Fla. Space Center, Fla. Mission Duration: 288 hours (12 days), 18 hours, Mission Duration: 288 hours (12 days), 18 hours, Mission Duration: 288 hours (12 days), 18 hours, 38 minutes 38 minutes 38 minutes Miles Traveled: Approximately 5.3 million statute miles Miles Traveled: Approximately 5.3 million statute miles Miles Traveled: Approximately 5.3 million statute miles Orbits of Earth: 202 Orbits of Earth: 202 Orbits of Earth: 202 Inclination: 51.6 degrees Inclination: 51.6 degrees Inclination: 51.6 degrees Orbital Altitude: 122 nautical miles Orbital Altitude: 122 nautical miles Orbital Altitude: 122 nautical miles Orbital ISS Rendezvous Altitude: Approximately Orbital ISS Rendezvous Altitude: Approximately Orbital ISS Rendezvous Altitude: Approximately 185 nautical miles 185 nautical miles 185 nautical miles Lift-Off Weight: 4,523,850 pounds Lift-Off Weight: 4,523,850 pounds Lift-Off Weight: 4,523,850 pounds Orbiter Weight at Lift-Off: 267,001 pounds Orbiter Weight at Lift-Off: 267,001 pounds Orbiter Weight at Lift-Off: 267,001 pounds Payload Weight Up: 29,280 pounds Payload Weight Up: 29,280 pounds Payload Weight Up: 29,280 pounds Orbiter Weight at Landing: 225,715 pounds Orbiter Weight at Landing: 225,715 pounds Orbiter Weight at Landing: 225,715 pounds Payload Weight Down: 24,508 pounds Payload Weight Down: 24,508 pounds Payload Weight Down: 24,508 pounds Landed: 9:14 a.m. EDT, concrete runway 15, Kennedy Landed: 9:14 a.m. EDT, concrete runway 15, Kennedy Landed: 9:14 a.m. EDT, concrete runway 15, Kennedy Space Center, Fla. Space Center, Fla. Space Center, Fla.

Y-98 Y-98 Y-98 STS-121 Mission Facts (Cont) STS-121 Mission Facts (Cont) STS-121 Mission Facts (Cont) Payload: ISS Assembly Flight ULF1.1; second Return-to- Payload: ISS Assembly Flight ULF1.1; second Return-to- Payload: ISS Assembly Flight ULF1.1; second Return-to- Flight mission; Leonardo Multi-Purpose Logistics Flight mission; Leonardo Multi-Purpose Logistics Flight mission; Leonardo Multi-Purpose Logistics Module carrying the Minus Eighty-Degrees Centi- Module carrying the Minus Eighty-Degrees Centi- Module carrying the Minus Eighty-Degrees Centi- grade Laboratory Freezer for ISS (MELFI); Integrat- grade Laboratory Freezer for ISS (MELFI); Integrat- grade Laboratory Freezer for ISS (MELFI); Integrat- ed Cargo Carrier (ICC); Lightweight Multi-Purpose ed Cargo Carrier (ICC); Lightweight Multi-Purpose ed Cargo Carrier (ICC); Lightweight Multi-Purpose Experiment Support Structure Carrier (LMC) Experiment Support Structure Carrier (LMC) Experiment Support Structure Carrier (LMC) Highlight: Before docking with the ISS, Lindsey per- Highlight: Before docking with the ISS, Lindsey per- Highlight: Before docking with the ISS, Lindsey per- formed a 360-degree backflip approximately 600 formed a 360-degree backflip approximately 600 formed a 360-degree backflip approximately 600 feet below the station, allowing ISS crew members feet below the station, allowing ISS crew members feet below the station, allowing ISS crew members to photograph the underside of Discovery and its to photograph the underside of Discovery and its to photograph the underside of Discovery and its heat-resistant tiles in detail. heat-resistant tiles in detail. heat-resistant tiles in detail. Extravehicular Activity (EVA) conducted by team of Extravehicular Activity (EVA) conducted by team of Extravehicular Activity (EVA) conducted by team of Piers Sellers and Michael Fossum. EVA 1, 7 hours, Piers Sellers and Michael Fossum. EVA 1, 7 hours, Piers Sellers and Michael Fossum. EVA 1, 7 hours, 31 minutes; Sellers and Fossum installed a blade 31 minutes; Sellers and Fossum installed a blade 31 minutes; Sellers and Fossum installed a blade blocker in the zenith interface umbilical assembly blocker in the zenith interface umbilical assembly blocker in the zenith interface umbilical assembly to protect the power, data, and video cable, then to protect the power, data, and video cable, then to protect the power, data, and video cable, then rerouted the cable through the IUA so the mobile rerouted the cable through the IUA so the mobile rerouted the cable through the IUA so the mobile transporter rail car could be moved into position transporter rail car could be moved into position transporter rail car could be moved into position on the truss. In addition, they tested the capability on the truss. In addition, they tested the capability on the truss. In addition, they tested the capability of the space shuttle’s robotic arm and its 50-foot of the space shuttle’s robotic arm and its 50-foot of the space shuttle’s robotic arm and its 50-foot extension—the orbiter boom sensor system—to extension—the orbiter boom sensor system—to extension—the orbiter boom sensor system—to act as a platform for spacewalkers making repairs. act as a platform for spacewalkers making repairs. act as a platform for spacewalkers making repairs. EVA 2, 6 hours, 47 minutes; Sellers and Fossum EVA 2, 6 hours, 47 minutes; Sellers and Fossum EVA 2, 6 hours, 47 minutes; Sellers and Fossum replaced the nadir-side trailing umbilical system replaced the nadir-side trailing umbilical system replaced the nadir-side trailing umbilical system (TUS) to restore the mobile transporter rail car to full (TUS) to restore the mobile transporter rail car to full (TUS) to restore the mobile transporter rail car to full operation and delivered a spare pump module for operation and delivered a spare pump module for operation and delivered a spare pump module for the ISS cooling system. EVA 3, 7 hours, 11 minutes; the ISS cooling system. EVA 3, 7 hours, 11 minutes; the ISS cooling system. EVA 3, 7 hours, 11 minutes; Sellers and Fossum tested techniques to inspect Sellers and Fossum tested techniques to inspect Sellers and Fossum tested techniques to inspect and repair damage to an orbiter’s heat shield, and repair damage to an orbiter’s heat shield, and repair damage to an orbiter’s heat shield, including test of a repair material known as NOAX including test of a repair material known as NOAX including test of a repair material known as NOAX (non-oxide adhesive experimental), a pre-ceramic (non-oxide adhesive experimental), a pre-ceramic (non-oxide adhesive experimental), a pre-ceramic polymer sealant containing carbon-silicon carbide polymer sealant containing carbon-silicon carbide polymer sealant containing carbon-silicon carbide powder. powder. powder.

STS-115 Mission Facts — Atlantis — STS-115 Mission Facts — Atlantis — STS-115 Mission Facts — Atlantis — Sept. 9–21, 2006 Sept. 9–21, 2006 Sept. 9–21, 2006

Commander: Brent W. Jett Commander: Brent W. Jett Commander: Brent W. Jett Pilot: Christopher J. Ferguson Pilot: Christopher J. Ferguson Pilot: Christopher J. Ferguson Mission Specialist: Joseph R. Tanner Mission Specialist: Joseph R. Tanner Mission Specialist: Joseph R. Tanner Mission Specialist: Daniel C. Burbank Mission Specialist: Daniel C. Burbank Mission Specialist: Daniel C. Burbank Mission Specialist: Steven G. MacLean, Canadian Space Mission Specialist: Steven G. MacLean, Canadian Space Mission Specialist: Steven G. MacLean, Canadian Space Agency (CSA) Agency (CSA) Agency (CSA) Mission Specialist: Heidemarie M. Stefanyshyn-Piper Mission Specialist: Heidemarie M. Stefanyshyn-Piper Mission Specialist: Heidemarie M. Stefanyshyn-Piper Launched: 11:15 a.m. EDT, launch pad 39B, Kennedy Launched: 11:15 a.m. EDT, launch pad 39B, Kennedy Launched: 11:15 a.m. EDT, launch pad 39B, Kennedy Space Center, Fla. Space Center, Fla. Space Center, Fla. Mission Duration: 264 hours (11 days), 19 hours, Mission Duration: 264 hours (11 days), 19 hours, Mission Duration: 264 hours (11 days), 19 hours, 6 minutes 6 minutes 6 minutes Miles Traveled: Approximately 4.9 million statute miles Miles Traveled: Approximately 4.9 million statute miles Miles Traveled: Approximately 4.9 million statute miles Orbits of Earth: 187 Orbits of Earth: 187 Orbits of Earth: 187 Inclination: 51.6 degrees Inclination: 51.6 degrees Inclination: 51.6 degrees Orbital Altitude: 122 nautical miles Orbital Altitude: 122 nautical miles Orbital Altitude: 122 nautical miles Orbital ISS Rendezvous Altitude: Approximately Orbital ISS Rendezvous Altitude: Approximately Orbital ISS Rendezvous Altitude: Approximately 185 nautical miles 185 nautical miles 185 nautical miles

Y-99 Y-99 Y-99 STS-115 Mission Facts (Cont) STS-115 Mission Facts (Cont) STS-115 Mission Facts (Cont)

Lift-Off Weight: 4,526,580 pounds Lift-Off Weight: 4,526,580 pounds Lift-Off Weight: 4,526,580 pounds Orbiter Weight at Lift-Off: 270,612 pounds Orbiter Weight at Lift-Off: 270,612 pounds Orbiter Weight at Lift-Off: 270,612 pounds Payload Weight Up: 35,758 pounds Payload Weight Up: 35,758 pounds Payload Weight Up: 35,758 pounds Orbiter Weight at Landing: 199,679 pounds Orbiter Weight at Landing: 199,679 pounds Orbiter Weight at Landing: 199,679 pounds Payload Weight Down: 978 pounds Payload Weight Down: 978 pounds Payload Weight Down: 978 pounds Landed: 6:21 a.m. EDT, concrete runway 33, Kennedy Landed: 6:21 a.m. EDT, concrete runway 33, Kennedy Landed: 6:21 a.m. EDT, concrete runway 33, Kennedy Space Center, Fla. Space Center, Fla. Space Center, Fla. Payload: ISS Assembly Flight 12A; ITS P3 and P4, Payload: ISS Assembly Flight 12A; ITS P3 and P4, Payload: ISS Assembly Flight 12A; ITS P3 and P4, second port truss segment, second set of solar second port truss segment, second set of solar second port truss segment, second set of solar arrays and batteries. This addition added 45 feet to arrays and batteries. This addition added 45 feet to arrays and batteries. This addition added 45 feet to the ISS and increased the wingspan to more than the ISS and increased the wingspan to more than the ISS and increased the wingspan to more than 240 feet. The solar arrays will double power to the 240 feet. The solar arrays will double power to the 240 feet. The solar arrays will double power to the ISS when brought online during mission STS-116. ISS when brought online during mission STS-116. ISS when brought online during mission STS-116. Extravehicular Activity (EVA) conducted by team of Extravehicular Activity (EVA) conducted by team of Extravehicular Activity (EVA) conducted by team of Heidemarie M. Stefanyshyn-Piper and Joe Tanner Heidemarie M. Stefanyshyn-Piper and Joe Tanner Heidemarie M. Stefanyshyn-Piper and Joe Tanner and team of Dan Burbank and Steve MacLean. EVA and team of Dan Burbank and Steve MacLean. EVA and team of Dan Burbank and Steve MacLean. EVA 1, 6 hours, 26 minutes; Piper and Tanner connected 1, 6 hours, 26 minutes; Piper and Tanner connected 1, 6 hours, 26 minutes; Piper and Tanner connected power cables on the truss and released the launch power cables on the truss and released the launch power cables on the truss and released the launch restraints on the solar array blanket box, beta restraints on the solar array blanket box, beta restraints on the solar array blanket box, beta gimbal assembly, and solar array wings. They also gimbal assembly, and solar array wings. They also gimbal assembly, and solar array wings. They also configured the solar alpha rotary joint (SARJ), an configured the solar alpha rotary joint (SARJ), an configured the solar alpha rotary joint (SARJ), an automobile-sized joint that allows the station’s solar automobile-sized joint that allows the station’s solar automobile-sized joint that allows the station’s solar arrays to turn and point toward the Sun. EVA 2, 7 arrays to turn and point toward the Sun. EVA 2, 7 arrays to turn and point toward the Sun. EVA 2, 7 hours, 11 minutes; Burbank and MacLean devoted hours, 11 minutes; Burbank and MacLean devoted hours, 11 minutes; Burbank and MacLean devoted the spacewalk to the final tasks required for activa- the spacewalk to the final tasks required for activa- the spacewalk to the final tasks required for activa- tion of the SARJ. EVA 3, 6 hours, 42 minutes; Piper tion of the SARJ. EVA 3, 6 hours, 42 minutes; Piper tion of the SARJ. EVA 3, 6 hours, 42 minutes; Piper and Tanner installed bolt retainers on the P6 beta and Tanner installed bolt retainers on the P6 beta and Tanner installed bolt retainers on the P6 beta gimbal assembly, which helps to orient the pitch of gimbal assembly, which helps to orient the pitch of gimbal assembly, which helps to orient the pitch of the solar array wings, and retrieved the Materials on the solar array wings, and retrieved the Materials on the solar array wings, and retrieved the Materials on the International Space Station Experiment 5. the International Space Station Experiment 5. the International Space Station Experiment 5. Of Note: The shuttle critical systems, including its heat Of Note: The shuttle critical systems, including its heat Of Note: The shuttle critical systems, including its heat shield, were inspected three times during the shield, were inspected three times during the shield, were inspected three times during the mission using the orbiter boom sensor system, the mission using the orbiter boom sensor system, the mission using the orbiter boom sensor system, the 50-foot-long extension for the shuttle’s robotic arm. 50-foot-long extension for the shuttle’s robotic arm. 50-foot-long extension for the shuttle’s robotic arm. In addition, a new procedure called a “camp out” In addition, a new procedure called a “camp out” In addition, a new procedure called a “camp out” was implemented in which astronauts slept in the was implemented in which astronauts slept in the was implemented in which astronauts slept in the Quest airlock prior to their spacewalks. The process Quest airlock prior to their spacewalks. The process Quest airlock prior to their spacewalks. The process shortens the “prebreathe” time during which nitro- shortens the “prebreathe” time during which nitro- shortens the “prebreathe” time during which nitro- gen is purged from the astronauts’ systems and air gen is purged from the astronauts’ systems and air gen is purged from the astronauts’ systems and air pressure is lowered to 10.2 psi so the spacewalkers pressure is lowered to 10.2 psi so the spacewalkers pressure is lowered to 10.2 psi so the spacewalkers avoid the condition known as the bends. On each avoid the condition known as the bends. On each avoid the condition known as the bends. On each of the three spacewalks, the astronauts were able of the three spacewalks, the astronauts were able of the three spacewalks, the astronauts were able to perform more than the number of scheduled to perform more than the number of scheduled to perform more than the number of scheduled activities. activities. activities.

Y-100 Y-100 Y-100 STS-116 Mission Facts — Discovery — STS-116 Mission Facts — Discovery — STS-116 Mission Facts — Discovery — Dec. 9–22, 2006 Dec. 9–22, 2006 Dec. 9–22, 2006

Commander: Mark L. Polansky Commander: Mark L. Polansky Commander: Mark L. Polansky Pilot: William A. Oefelein Pilot: William A. Oefelein Pilot: William A. Oefelein Mission Specialist: Robert L. Curbeam Jr. Mission Specialist: Robert L. Curbeam Jr. Mission Specialist: Robert L. Curbeam Jr. Mission Specialist: Joan E. Higginbotham Mission Specialist: Joan E. Higginbotham Mission Specialist: Joan E. Higginbotham Mission Specialist: Nicholas J.M. Patrick Mission Specialist: Nicholas J.M. Patrick Mission Specialist: Nicholas J.M. Patrick Mission Specialist: Christer Fuglesang, European Space Mission Specialist: Christer Fuglesang, European Space Mission Specialist: Christer Fuglesang, European Space Agency (ESA) Agency (ESA) Agency (ESA) ISS Crew Member: Sunita L. Williams—up only ISS Crew Member: Sunita L. Williams—up only ISS Crew Member: Sunita L. Williams—up only ISS Crew Member: Thomas Reiter—down only ISS Crew Member: Thomas Reiter—down only ISS Crew Member: Thomas Reiter—down only Launched: 8:47 p.m. EDT, launch pad 39B, Kennedy Launched: 8:47 p.m. EDT, launch pad 39B, Kennedy Launched: 8:47 p.m. EDT, launch pad 39B, Kennedy Space Center, Fla. Space Center, Fla. Space Center, Fla. Mission Duration: 288 hours (12 days), 20 hours, Mission Duration: 288 hours (12 days), 20 hours, Mission Duration: 288 hours (12 days), 20 hours, 44 minutes 44 minutes 44 minutes Miles Traveled: Approximately 5.3 million statute miles Miles Traveled: Approximately 5.3 million statute miles Miles Traveled: Approximately 5.3 million statute miles Orbits of Earth: 204 Orbits of Earth: 204 Orbits of Earth: 204 Inclination: 51.6 degrees Inclination: 51.6 degrees Inclination: 51.6 degrees Orbital Altitude: 122 nautical miles Orbital Altitude: 122 nautical miles Orbital Altitude: 122 nautical miles Orbital ISS Rendezvous Altitude: Approximately 185 Orbital ISS Rendezvous Altitude: Approximately 185 Orbital ISS Rendezvous Altitude: Approximately 185 nautical miles nautical miles nautical miles Lift-Off Weight: 4,520,334 pounds Lift-Off Weight: 4,520,334 pounds Lift-Off Weight: 4,520,334 pounds Orbiter Weight at Lift-Off: 265,275 pounds Orbiter Weight at Lift-Off: 265,275 pounds Orbiter Weight at Lift-Off: 265,275 pounds Payload Weight Up: 35,720 pounds Payload Weight Up: 35,720 pounds Payload Weight Up: 35,720 pounds Orbiter Weight at Landing: 225,431 pounds Orbiter Weight at Landing: 225,431 pounds Orbiter Weight at Landing: 225,431 pounds Payload Weight Down: 3,705 pounds Payload Weight Down: 3,705 pounds Payload Weight Down: 3,705 pounds Landed: 5:32 p.m. EDT, concrete runway 15, Kennedy Landed: 5:32 p.m. EDT, concrete runway 15, Kennedy Landed: 5:32 p.m. EDT, concrete runway 15, Kennedy Space Center, Fla. Space Center, Fla. Space Center, Fla. Payload: ISS Assembly Flight 12A.1; ITS P5, third port Payload: ISS Assembly Flight 12A.1; ITS P5, third port Payload: ISS Assembly Flight 12A.1; ITS P5, third port truss segment; SPACEHAB single cargo module; In- truss segment; SPACEHAB single cargo module; In- truss segment; SPACEHAB single cargo module; In- tegrated Cargo Carrier (ICC); Microelectromechani- tegrated Cargo Carrier (ICC); Microelectromechani- tegrated Cargo Carrier (ICC); Microelectromechani- cal System-Based PICOSAT Inspector (MEPSI) cal System-Based PICOSAT Inspector (MEPSI) cal System-Based PICOSAT Inspector (MEPSI) microsatellite; Radar Fence Transponder (RAFT) microsatellite; Radar Fence Transponder (RAFT) microsatellite; Radar Fence Transponder (RAFT) microsatellite; Atmospheric Neutral Density Experi- microsatellite; Atmospheric Neutral Density Experi- microsatellite; Atmospheric Neutral Density Experi- ment (ANDE) microsatellite; ISS crew exchange ment (ANDE) microsatellite; ISS crew exchange ment (ANDE) microsatellite; ISS crew exchange Extravehicular Activity (EVA) conducted by team of Extravehicular Activity (EVA) conducted by team of Extravehicular Activity (EVA) conducted by team of Robert Curbeam and Christer Fuglesang and team Robert Curbeam and Christer Fuglesang and team Robert Curbeam and Christer Fuglesang and team of Robert Curbeam and Sunita Williams. EVA 1, of Robert Curbeam and Sunita Williams. EVA 1, of Robert Curbeam and Sunita Williams. EVA 1, 6 hours, 36 minutes; Curbeam and Fuglesang 6 hours, 36 minutes; Curbeam and Fuglesang 6 hours, 36 minutes; Curbeam and Fuglesang attached the two-ton P5 segment, which had been attached the two-ton P5 segment, which had been attached the two-ton P5 segment, which had been unberthed the day before using the shuttle’s robotic unberthed the day before using the shuttle’s robotic unberthed the day before using the shuttle’s robotic arm to remove it from the orbiter’s payload bay and arm to remove it from the orbiter’s payload bay and arm to remove it from the orbiter’s payload bay and hand it off to the station arm. Guided by Curbeam hand it off to the station arm. Guided by Curbeam hand it off to the station arm. Guided by Curbeam and Fuglesang, Joan Higginbotham maneuvered and Fuglesang, Joan Higginbotham maneuvered and Fuglesang, Joan Higginbotham maneuvered the P5 into place. EVA 2, 5 hours, 0 minute; the P5 into place. EVA 2, 5 hours, 0 minute; the P5 into place. EVA 2, 5 hours, 0 minute; Curbeam and Fuglesang reconfigured two of the Curbeam and Fuglesang reconfigured two of the Curbeam and Fuglesang reconfigured two of the station’s four power channels, channels 2 and 3. station’s four power channels, channels 2 and 3. station’s four power channels, channels 2 and 3. EVA 3, 7 hours, 31 minutes; Curbeam and Sunita EVA 3, 7 hours, 31 minutes; Curbeam and Sunita EVA 3, 7 hours, 31 minutes; Curbeam and Sunita Williams reconfigured the station’s power channels Williams reconfigured the station’s power channels Williams reconfigured the station’s power channels 1 and 4, setting the stage for future installation of 1 and 4, setting the stage for future installation of 1 and 4, setting the stage for future installation of additional solar arrays and science modules, includ- additional solar arrays and science modules, includ- additional solar arrays and science modules, includ- ing those of international partners. EVA 4, 6 hours, ing those of international partners. EVA 4, 6 hours, ing those of international partners. EVA 4, 6 hours, 38 minutes; The P6 solar array wing had been 38 minutes; The P6 solar array wing had been 38 minutes; The P6 solar array wing had been extended in space for six years. The array panels extended in space for six years. The array panels extended in space for six years. The array panels

Y-101 Y-101 Y-101 STS-116 Mission Facts (Cont) STS-116 Mission Facts (Cont) STS-116 Mission Facts (Cont)

would not fully retract because of a snagged would not fully retract because of a snagged would not fully retract because of a snagged guide wire, necessitating the addition of a fourth guide wire, necessitating the addition of a fourth guide wire, necessitating the addition of a fourth spacewalk to free the partially retracted solar array spacewalk to free the partially retracted solar array spacewalk to free the partially retracted solar array so it would fully fold. Curbeam and Fuglesang so it would fully fold. Curbeam and Fuglesang so it would fully fold. Curbeam and Fuglesang guided the P6 solar array wing inside its blanket guided the P6 solar array wing inside its blanket guided the P6 solar array wing inside its blanket box. Subsequently, the Solar Alpha Rotary Joint box. Subsequently, the Solar Alpha Rotary Joint box. Subsequently, the Solar Alpha Rotary Joint was powered up, enabling it to begin turning the P4 was powered up, enabling it to begin turning the P4 was powered up, enabling it to begin turning the P4 truss solar array wings, which had been installed truss solar array wings, which had been installed truss solar array wings, which had been installed in September 2006, allowing the arrays to track the in September 2006, allowing the arrays to track the in September 2006, allowing the arrays to track the sun as it rises and sets with each station orbit. sun as it rises and sets with each station orbit. sun as it rises and sets with each station orbit. Of Note: First nighttime launch in more than four years. Of Note: First nighttime launch in more than four years. Of Note: First nighttime launch in more than four years. Curbeam set a shuttle program record for the most Curbeam set a shuttle program record for the most Curbeam set a shuttle program record for the most spacewalks performed by one astronaut during a spacewalks performed by one astronaut during a spacewalks performed by one astronaut during a single mission. Mission Control sent approximately single mission. Mission Control sent approximately single mission. Mission Control sent approximately 17,900 commands during the mission, about 5,000 17,900 commands during the mission, about 5,000 17,900 commands during the mission, about 5,000 more commands than sent on any previous mis- more commands than sent on any previous mis- more commands than sent on any previous mis- sion. First use of Advanced Health Management sion. First use of Advanced Health Management sion. First use of Advanced Health Management System (AHMS), developed at Marshall Space System (AHMS), developed at Marshall Space System (AHMS), developed at Marshall Space Flight Center to improve Space Shuttle Main Engine Flight Center to improve Space Shuttle Main Engine Flight Center to improve Space Shuttle Main Engine safety. AHMS was used on STS-116 to collect safety. AHMS was used on STS-116 to collect safety. AHMS was used on STS-116 to collect performance data only, but on future flights the performance data only, but on future flights the performance data only, but on future flights the AHMS will cut off an SSME if the AHMS detects that AHMS will cut off an SSME if the AHMS detects that AHMS will cut off an SSME if the AHMS detects that a failure is about to occur. a failure is about to occur. a failure is about to occur.

STS-117 Mission Facts — Atlantis — STS-117 Mission Facts — Atlantis — STS-117 Mission Facts — Atlantis — June 8–22, 2007 June 8–22, 2007 June 8–22, 2007

Commander: Frederick W. Sturckow Commander: Frederick W. Sturckow Commander: Frederick W. Sturckow Pilot: Lee J. Archambault Pilot: Lee J. Archambault Pilot: Lee J. Archambault Mission Specialist: James F. Reilly II Mission Specialist: James F. Reilly II Mission Specialist: James F. Reilly II Mission Specialist: Steven R. Swanson Mission Specialist: Steven R. Swanson Mission Specialist: Steven R. Swanson Mission Specialist: Patrick G. Forrester Mission Specialist: Patrick G. Forrester Mission Specialist: Patrick G. Forrester Mission Specialist: John D. (Danny) Olivas Mission Specialist: John D. (Danny) Olivas Mission Specialist: John D. (Danny) Olivas ISS Crew Member: Clayton C. Anderson—up only ISS Crew Member: Clayton C. Anderson—up only ISS Crew Member: Clayton C. Anderson—up only ISS Crew Member: Sunita L. Williams—down only ISS Crew Member: Sunita L. Williams—down only ISS Crew Member: Sunita L. Williams—down only Launched: 7:38 p.m. EDT, launch pad 39A, Kennedy Launched: 7:38 p.m. EDT, launch pad 39A, Kennedy Launched: 7:38 p.m. EDT, launch pad 39A, Kennedy Space Center, Fla. Space Center, Fla. Space Center, Fla. Mission Duration: 312 hours (13 days), 20 hours, Mission Duration: 312 hours (13 days), 20 hours, Mission Duration: 312 hours (13 days), 20 hours, 12 minutes 12 minutes 12 minutes Miles Traveled: Approximately 5.8 million statute miles Miles Traveled: Approximately 5.8 million statute miles Miles Traveled: Approximately 5.8 million statute miles Orbits of Earth: 219 Orbits of Earth: 219 Orbits of Earth: 219 Inclination: 51.6 degrees Inclination: 51.6 degrees Inclination: 51.6 degrees Orbital Altitude: 122 nautical miles Orbital Altitude: 122 nautical miles Orbital Altitude: 122 nautical miles Orbital ISS Rendezvous Altitude: Approximately 220 Orbital ISS Rendezvous Altitude: Approximately 220 Orbital ISS Rendezvous Altitude: Approximately 220 nautical miles nautical miles nautical miles Lift-Off Weight: 4,525,519 pounds Lift-Off Weight: 4,525,519 pounds Lift-Off Weight: 4,525,519 pounds Orbiter Weight at Lift-Off: 270,517 pounds Orbiter Weight at Lift-Off: 270,517 pounds Orbiter Weight at Lift-Off: 270,517 pounds Payload Weight Up: 42,671 pounds Payload Weight Up: 42,671 pounds Payload Weight Up: 42,671 pounds Orbiter Weight at Landing: 199,501 pounds Orbiter Weight at Landing: 199,501 pounds Orbiter Weight at Landing: 199,501 pounds Payload Weight Down: 1,057 pounds Payload Weight Down: 1,057 pounds Payload Weight Down: 1,057 pounds Landed: 3:49 p.m. EDT, concrete runway 22, Edwards Air Landed: 3:49 p.m. EDT, concrete runway 22, Edwards Air Landed: 3:49 p.m. EDT, concrete runway 22, Edwards Air Force Base, Calif. Force Base, Calif. Force Base, Calif.

Y-102 Y-102 Y-102 STS-117 Mission Facts (Cont) STS-117 Mission Facts (Cont) STS-117 Mission Facts (Cont)

Payload: ISS Assembly Flight 13A; ITS S3 and S4, sec- Payload: ISS Assembly Flight 13A; ITS S3 and S4, sec- Payload: ISS Assembly Flight 13A; ITS S3 and S4, sec- ond starboard truss segment, the heaviest station ond starboard truss segment, the heaviest station ond starboard truss segment, the heaviest station payload the space shuttle has carried to date; third payload the space shuttle has carried to date; third payload the space shuttle has carried to date; third set of solar arrays and batteries; ISS crew exchange set of solar arrays and batteries; ISS crew exchange set of solar arrays and batteries; ISS crew exchange Extravehicular Activity (EVA) conducted by team of Extravehicular Activity (EVA) conducted by team of Extravehicular Activity (EVA) conducted by team of James Reilly and Danny Olivas and team of Patrick James Reilly and Danny Olivas and team of Patrick James Reilly and Danny Olivas and team of Patrick Forrester and Steve Swanson. EVA 1, 6 hours, 15 Forrester and Steve Swanson. EVA 1, 6 hours, 15 Forrester and Steve Swanson. EVA 1, 6 hours, 15 minutes; previously, Lee Archambault and Patrick minutes; previously, Lee Archambault and Patrick minutes; previously, Lee Archambault and Patrick Forrester had used the shuttle’s robotic arm to Forrester had used the shuttle’s robotic arm to Forrester had used the shuttle’s robotic arm to grapple the S3/S4 truss, lift it from its berth in the grapple the S3/S4 truss, lift it from its berth in the grapple the S3/S4 truss, lift it from its berth in the payload bay, and maneuver it for handover to the payload bay, and maneuver it for handover to the payload bay, and maneuver it for handover to the station’s Canadarm2, manned by Suni Williams. station’s Canadarm2, manned by Suni Williams. station’s Canadarm2, manned by Suni Williams. During their spacewalk, Reilly and Olivas focused During their spacewalk, Reilly and Olivas focused During their spacewalk, Reilly and Olivas focused on the final attachment of bolts, cables, and con- on the final attachment of bolts, cables, and con- on the final attachment of bolts, cables, and con- nectors to begin activation of the truss and ready it nectors to begin activation of the truss and ready it nectors to begin activation of the truss and ready it for deployment of its solar arrays. EVA 2, 7 hours, for deployment of its solar arrays. EVA 2, 7 hours, for deployment of its solar arrays. EVA 2, 7 hours, 16 minutes; Forrester and Swanson helped retract 16 minutes; Forrester and Swanson helped retract 16 minutes; Forrester and Swanson helped retract the 115-ft P6 solar array, which will be relocated the 115-ft P6 solar array, which will be relocated the 115-ft P6 solar array, which will be relocated during a future assembly mission, to clear the path during a future assembly mission, to clear the path during a future assembly mission, to clear the path for the new array, then removed all of the launch for the new array, then removed all of the launch for the new array, then removed all of the launch locks holding the solar alpha rotary joint in place, locks holding the solar alpha rotary joint in place, locks holding the solar alpha rotary joint in place, freeing it to rotate, enabling the new solar array freeing it to rotate, enabling the new solar array freeing it to rotate, enabling the new solar array wings on S4 to track the sun as ISS orbits the Earth. wings on S4 to track the sun as ISS orbits the Earth. wings on S4 to track the sun as ISS orbits the Earth. The arrays provide a total power capability of 60 The arrays provide a total power capability of 60 The arrays provide a total power capability of 60 kW, equivalent to the power used by 40 typical U.S. kW, equivalent to the power used by 40 typical U.S. kW, equivalent to the power used by 40 typical U.S. homes. EVA 3, 7 hours, 58 minutes; Reilly installed homes. EVA 3, 7 hours, 58 minutes; Reilly installed homes. EVA 3, 7 hours, 58 minutes; Reilly installed the hydrogen vent valve of a new oxygen generation the hydrogen vent valve of a new oxygen generation the hydrogen vent valve of a new oxygen generation system on the Destiny laboratory. Olivas completed system on the Destiny laboratory. Olivas completed system on the Destiny laboratory. Olivas completed a repair to a raised corner of a thermal insulation a repair to a raised corner of a thermal insulation a repair to a raised corner of a thermal insulation blanket that had come loose from the shuttle during blanket that had come loose from the shuttle during blanket that had come loose from the shuttle during launch. Olivas pressed down on the blanket and launch. Olivas pressed down on the blanket and launch. Olivas pressed down on the blanket and stapled one side of the 4- by 6-in. raised corner to stapled one side of the 4- by 6-in. raised corner to stapled one side of the 4- by 6-in. raised corner to an adjacent blanket. Olivas then pinned the other an adjacent blanket. Olivas then pinned the other an adjacent blanket. Olivas then pinned the other side of the blanket to a thermal tile. EVA 4, 6 hours, side of the blanket to a thermal tile. EVA 4, 6 hours, side of the blanket to a thermal tile. EVA 4, 6 hours, 29 minutes; Forrester and Swanson completed 29 minutes; Forrester and Swanson completed 29 minutes; Forrester and Swanson completed numerous tasks associated with the new truss numerous tasks associated with the new truss numerous tasks associated with the new truss segment, removed launch restraints on the SARJ to segment, removed launch restraints on the SARJ to segment, removed launch restraints on the SARJ to enable its rotation, and installed a debris shield on enable its rotation, and installed a debris shield on enable its rotation, and installed a debris shield on the Destiny laboratory. the Destiny laboratory. the Destiny laboratory. Of Note: Following a hailstorm at KSC on Feb. 26, 2007, Of Note: Following a hailstorm at KSC on Feb. 26, 2007, Of Note: Following a hailstorm at KSC on Feb. 26, 2007, inspections of the stack found damage to the inspections of the stack found damage to the inspections of the stack found damage to the orbiter and the external tank. Hailstones as large as orbiter and the external tank. Hailstones as large as orbiter and the external tank. Hailstones as large as golf balls had damaged ice frost ramps on the tank, golf balls had damaged ice frost ramps on the tank, golf balls had damaged ice frost ramps on the tank, caused minor surface damage to about 26 heat caused minor surface damage to about 26 heat caused minor surface damage to about 26 heat shield tiles on Atlantis’s left wing, and created more shield tiles on Atlantis’s left wing, and created more shield tiles on Atlantis’s left wing, and created more than 2,600 dents, divots, and gouges in the tank’s than 2,600 dents, divots, and gouges in the tank’s than 2,600 dents, divots, and gouges in the tank’s foam insulation, requiring technicians to spray an foam insulation, requiring technicians to spray an foam insulation, requiring technicians to spray an aerodynamically smooth layer of thermal insulation aerodynamically smooth layer of thermal insulation aerodynamically smooth layer of thermal insulation on the curved portion near the top of the tank. on the curved portion near the top of the tank. on the curved portion near the top of the tank. Suni Williams set a new record of 194 days for the Suni Williams set a new record of 194 days for the Suni Williams set a new record of 194 days for the longest single spaceflight by a female space trav- longest single spaceflight by a female space trav- longest single spaceflight by a female space trav- eler, breaking the record of 188 days previously set eler, breaking the record of 188 days previously set eler, breaking the record of 188 days previously set by Shannon Lucid on her assignment aboard the by Shannon Lucid on her assignment aboard the by Shannon Lucid on her assignment aboard the Mir space station in 1996. Mir space station in 1996. Mir space station in 1996.

Y-103 Y-103 Y-103 STS-118 Mission Facts — Endeavour — STS-118 Mission Facts — Endeavour — STS-118 Mission Facts — Endeavour — Aug. 8–21, 2007 Aug. 8–21, 2007 Aug. 8–21, 2007

Commander: Scott J. Kelly Commander: Scott J. Kelly Commander: Scott J. Kelly Pilot: Charles O. Hobaugh Pilot: Charles O. Hobaugh Pilot: Charles O. Hobaugh Mission Specialist: Dafydd (Dave) R. Williams, Canadian Mission Specialist: Dafydd (Dave) R. Williams, Canadian Mission Specialist: Dafydd (Dave) R. Williams, Canadian Space Agency Space Agency Space Agency Mission Specialist: Barbara R. Morgan Mission Specialist: Barbara R. Morgan Mission Specialist: Barbara R. Morgan Mission Specialist: Richard A. Mastracchio Mission Specialist: Richard A. Mastracchio Mission Specialist: Richard A. Mastracchio Mission Specialist: Tracy E. Caldwell Mission Specialist: Tracy E. Caldwell Mission Specialist: Tracy E. Caldwell Mission Specialist: Benjamin Alvin Drew Mission Specialist: Benjamin Alvin Drew Mission Specialist: Benjamin Alvin Drew Launched: 6:36 p.m. EDT, launch pad 39A, Kennedy Launched: 6:36 p.m. EDT, launch pad 39A, Kennedy Launched: 6:36 p.m. EDT, launch pad 39A, Kennedy Space Center, Fla. Space Center, Fla. Space Center, Fla. Mission Duration: 288 hours (12 days), 17 hours, Mission Duration: 288 hours (12 days), 17 hours, Mission Duration: 288 hours (12 days), 17 hours, 55 minutes 55 minutes 55 minutes Miles Traveled: Approximately 5.3 million statute miles Miles Traveled: Approximately 5.3 million statute miles Miles Traveled: Approximately 5.3 million statute miles Orbits of Earth: 202 Orbits of Earth: 202 Orbits of Earth: 202 Inclination: 51.6 degrees Inclination: 51.6 degrees Inclination: 51.6 degrees Orbital Altitude: 122 nautical miles Orbital Altitude: 122 nautical miles Orbital Altitude: 122 nautical miles Orbital ISS Rendezvous Altitude: Approximately 184 Orbital ISS Rendezvous Altitude: Approximately 184 Orbital ISS Rendezvous Altitude: Approximately 184 nautical miles nautical miles nautical miles Lift-Off Weight: 4,520,773 pounds Lift-Off Weight: 4,520,773 pounds Lift-Off Weight: 4,520,773 pounds Orbiter Weight at Lift-Off: 268,574 pounds Orbiter Weight at Lift-Off: 268,574 pounds Orbiter Weight at Lift-Off: 268,574 pounds Payload Weight Up: 23,899 pounds Payload Weight Up: 23,899 pounds Payload Weight Up: 23,899 pounds Orbiter Weight at Landing: 222,398 pounds Orbiter Weight at Landing: 222,398 pounds Orbiter Weight at Landing: 222,398 pounds Payload Weight Down: 12,385 pounds Payload Weight Down: 12,385 pounds Payload Weight Down: 12,385 pounds Landed: 12:33 p.m. EDT, concrete runway 15, Kennedy Landed: 12:33 p.m. EDT, concrete runway 15, Kennedy Landed: 12:33 p.m. EDT, concrete runway 15, Kennedy Space Center, Fla. Space Center, Fla. Space Center, Fla. Payload: ISS Assembly Flight 13A.1; ITS S5, third star- Payload: ISS Assembly Flight 13A.1; ITS S5, third star- Payload: ISS Assembly Flight 13A.1; ITS S5, third star- board truss segment; External Stowage Platform 3 board truss segment; External Stowage Platform 3 board truss segment; External Stowage Platform 3 (ESP-3); SPACEHAB single cargo module (ESP-3); SPACEHAB single cargo module (ESP-3); SPACEHAB single cargo module Extravehicular Activity (EVA) conducted by Richard Extravehicular Activity (EVA) conducted by Richard Extravehicular Activity (EVA) conducted by Richard Mastracchio, Dave Williams, and Clayton Ander- Mastracchio, Dave Williams, and Clayton Ander- Mastracchio, Dave Williams, and Clayton Ander- son. EVA 1, 6 hours, 17 minutes; Mastracchio and son. EVA 1, 6 hours, 17 minutes; Mastracchio and son. EVA 1, 6 hours, 17 minutes; Mastracchio and Williams attached the S5 segment of the station’s Williams attached the S5 segment of the station’s Williams attached the S5 segment of the station’s truss and continued preparations to relocate the P6 truss and continued preparations to relocate the P6 truss and continued preparations to relocate the P6 truss. EVA 2, 6 hours, 28 minutes; Mastracchio and truss. EVA 2, 6 hours, 28 minutes; Mastracchio and truss. EVA 2, 6 hours, 28 minutes; Mastracchio and Williams replaced a faulty Control Moment Gyro- Williams replaced a faulty Control Moment Gyro- Williams replaced a faulty Control Moment Gyro- scope (CMG), restoring the full four-CMG capability scope (CMG), restoring the full four-CMG capability scope (CMG), restoring the full four-CMG capability to help maintain ISS orientation. EVA 3, 5 hours, to help maintain ISS orientation. EVA 3, 5 hours, to help maintain ISS orientation. EVA 3, 5 hours, 28 minutes; Mastracchio and Anderson prepared 28 minutes; Mastracchio and Anderson prepared 28 minutes; Mastracchio and Anderson prepared the ISS for the next step in solar array deployment the ISS for the next step in solar array deployment the ISS for the next step in solar array deployment and voice communications system upgrades. The and voice communications system upgrades. The and voice communications system upgrades. The spacewalk ended early because of a perceived tear spacewalk ended early because of a perceived tear spacewalk ended early because of a perceived tear in Mastracchio’s glove. EVA 4, 5 hours, 2 minutes; in Mastracchio’s glove. EVA 4, 5 hours, 2 minutes; in Mastracchio’s glove. EVA 4, 5 hours, 2 minutes; Williams and Anderson installed an External Wire- Williams and Anderson installed an External Wire- Williams and Anderson installed an External Wire- less Instrumentation System antenna, installed a less Instrumentation System antenna, installed a less Instrumentation System antenna, installed a stand for the space shuttle’s robotic arm extension stand for the space shuttle’s robotic arm extension stand for the space shuttle’s robotic arm extension boom, and retrieved two containers of the Materials boom, and retrieved two containers of the Materials boom, and retrieved two containers of the Materials ISS Experiment. ISS Experiment. ISS Experiment.

Y-104 Y-104 Y-104 STS-118 Mission Facts (Cont) STS-118 Mission Facts (Cont) STS-118 Mission Facts (Cont)

Of Note: The Zarya module, the oldest ISS element, com- Of Note: The Zarya module, the oldest ISS element, com- Of Note: The Zarya module, the oldest ISS element, com- pleted its 50,000th orbit on Aug. 14. The Russian- pleted its 50,000th orbit on Aug. 14. The Russian- pleted its 50,000th orbit on Aug. 14. The Russian- built U.S. space station component’s docking ports built U.S. space station component’s docking ports built U.S. space station component’s docking ports accommodate Russian Soyuz piloted spacecraft accommodate Russian Soyuz piloted spacecraft accommodate Russian Soyuz piloted spacecraft and unpiloted Progress resupply spacecraft. and unpiloted Progress resupply spacecraft. and unpiloted Progress resupply spacecraft.

In a first for the ISS, astronauts installed the ESP-3 In a first for the ISS, astronauts installed the ESP-3 In a first for the ISS, astronauts installed the ESP-3 using only the station and shuttle robotic arms. The using only the station and shuttle robotic arms. The using only the station and shuttle robotic arms. The installation of the two previous stowage platforms, installation of the two previous stowage platforms, installation of the two previous stowage platforms, one on Destiny and one on Quest, required the help one on Destiny and one on Quest, required the help one on Destiny and one on Quest, required the help of spacewalking astronauts. of spacewalking astronauts. of spacewalking astronauts.

First flight of Endeavour following a 4-year modern- First flight of Endeavour following a 4-year modern- First flight of Endeavour following a 4-year modern- ization during which 1,670,000 parts were replaced ization during which 1,670,000 parts were replaced ization during which 1,670,000 parts were replaced and 194 modifications were made. STS-118 marked and 194 modifications were made. STS-118 marked and 194 modifications were made. STS-118 marked the first use of the Station-Shuttle Power Transfer the first use of the Station-Shuttle Power Transfer the first use of the Station-Shuttle Power Transfer System (SSPTS), a new system designed to allow a System (SSPTS), a new system designed to allow a System (SSPTS), a new system designed to allow a docked space shuttle to draw power from the ISS, docked space shuttle to draw power from the ISS, docked space shuttle to draw power from the ISS, which then enables a space shuttle to add three which then enables a space shuttle to add three which then enables a space shuttle to add three days to a mission. Future missions could gain as days to a mission. Future missions could gain as days to a mission. Future missions could gain as many as six extra days once all the ISS solar arrays many as six extra days once all the ISS solar arrays many as six extra days once all the ISS solar arrays are installed. Although STS-118 had the capability are installed. Although STS-118 had the capability are installed. Although STS-118 had the capability for a 14-day mission, the mission was ended one for a 14-day mission, the mission was ended one for a 14-day mission, the mission was ended one day early because of potential impacts at landing day early because of potential impacts at landing day early because of potential impacts at landing from Hurricane Dean. from Hurricane Dean. from Hurricane Dean.

Barbara Morgan, trained as the backup to Christa Barbara Morgan, trained as the backup to Christa Barbara Morgan, trained as the backup to Christa McAuliffe, NASA’s Teacher in Space candidate, be- McAuliffe, NASA’s Teacher in Space candidate, be- McAuliffe, NASA’s Teacher in Space candidate, be- came the first Mission Specialist Educator in space came the first Mission Specialist Educator in space came the first Mission Specialist Educator in space on STS-118. on STS-118. on STS-118.

STS-120 Mission Facts — Discovery — STS-120 Mission Facts — Discovery — STS-120 Mission Facts — Discovery — Oct. 23–Nov. 7, 2007 Oct. 23–Nov. 7, 2007 Oct. 23–Nov. 7, 2007

Commander: Pamela A. Melroy Commander: Pamela A. Melroy Commander: Pamela A. Melroy Pilot: George D. Zamka Pilot: George D. Zamka Pilot: George D. Zamka Mission Specialist: Scott E. Parazynski Mission Specialist: Scott E. Parazynski Mission Specialist: Scott E. Parazynski Mission Specialist: Douglas H. Wheelock Mission Specialist: Douglas H. Wheelock Mission Specialist: Douglas H. Wheelock Mission Specialist: Stephanie D. Wilson Mission Specialist: Stephanie D. Wilson Mission Specialist: Stephanie D. Wilson Mission Specialist: Paolo A. Nespoli, European Space Mission Specialist: Paolo A. Nespoli, European Space Mission Specialist: Paolo A. Nespoli, European Space Agency (ESA) Agency (ESA) Agency (ESA) ISS Crew Member: Daniel M. Tani—up only ISS Crew Member: Daniel M. Tani—up only ISS Crew Member: Daniel M. Tani—up only ISS Crew Member: Clayton C. Anderson—down only ISS Crew Member: Clayton C. Anderson—down only ISS Crew Member: Clayton C. Anderson—down only Launched: 11:38 a.m. EDT, launch pad 39A, Kennedy Launched: 11:38 a.m. EDT, launch pad 39A, Kennedy Launched: 11:38 a.m. EDT, launch pad 39A, Kennedy Space Center, Fla. Space Center, Fla. Space Center, Fla. Mission Duration: 360 hours (15 days), 2 hours, Mission Duration: 360 hours (15 days), 2 hours, Mission Duration: 360 hours (15 days), 2 hours, 23 minutes 23 minutes 23 minutes Miles Traveled: Approximately 6.25 million statute miles Miles Traveled: Approximately 6.25 million statute miles Miles Traveled: Approximately 6.25 million statute miles Orbits of Earth: 238 Orbits of Earth: 238 Orbits of Earth: 238 Inclination: 51.6 degrees Inclination: 51.6 degrees Inclination: 51.6 degrees Orbital Altitude: 122 nautical miles Orbital Altitude: 122 nautical miles Orbital Altitude: 122 nautical miles Orbital ISS Rendezvous Altitude: Approximately Orbital ISS Rendezvous Altitude: Approximately Orbital ISS Rendezvous Altitude: Approximately 210 nautical miles 210 nautical miles 210 nautical miles

Y-105 Y-105 Y-105 STS-120 Mission Facts (Cont) STS-120 Mission Facts (Cont) STS-120 Mission Facts (Cont)

Lift-Off Weight: 4,524,107 pounds Lift-Off Weight: 4,524,107 pounds Lift-Off Weight: 4,524,107 pounds Orbiter Weight at Lift-Off: 268,177 pounds Orbiter Weight at Lift-Off: 268,177 pounds Orbiter Weight at Lift-Off: 268,177 pounds Payload Weight Up: 33,813 pounds Payload Weight Up: 33,813 pounds Payload Weight Up: 33,813 pounds Orbiter Weight at Landing: 202,138 pounds Orbiter Weight at Landing: 202,138 pounds Orbiter Weight at Landing: 202,138 pounds Payload Weight Down: 2,020 pounds Payload Weight Down: 2,020 pounds Payload Weight Down: 2,020 pounds Landed: 1:01 p.m. EST, concrete runway 33, Landed: 1:01 p.m. EST, concrete runway 33, Landed: 1:01 p.m. EST, concrete runway 33, Kennedy Space Center, Fla. Kennedy Space Center, Fla. Kennedy Space Center, Fla. Payload: ISS Assembly Flight 10A; Node 2 connecting Payload: ISS Assembly Flight 10A; Node 2 connecting Payload: ISS Assembly Flight 10A; Node 2 connecting module; crew exchange module; crew exchange module; crew exchange Extravehicular Activity (EVA) conducted by Scott Extravehicular Activity (EVA) conducted by Scott Extravehicular Activity (EVA) conducted by Scott Parazynski, Doug Wheelock, and Daniel Tani. Parazynski, Doug Wheelock, and Daniel Tani. Parazynski, Doug Wheelock, and Daniel Tani. EVA 1, 6 hours, 14 minutes; Parazynski and EVA 1, 6 hours, 14 minutes; Parazynski and EVA 1, 6 hours, 14 minutes; Parazynski and Wheelock installed the Harmony module in its Wheelock installed the Harmony module in its Wheelock installed the Harmony module in its temporary location on the ISS and readied the P6 temporary location on the ISS and readied the P6 temporary location on the ISS and readied the P6 truss for its relocation. EVA 2, 6 hours, 33 minutes; truss for its relocation. EVA 2, 6 hours, 33 minutes; truss for its relocation. EVA 2, 6 hours, 33 minutes; Stephanie Wilson and Wheelock used Canadarm2 Stephanie Wilson and Wheelock used Canadarm2 Stephanie Wilson and Wheelock used Canadarm2 to grapple the P6 truss secured atop the Z1 truss. to grapple the P6 truss secured atop the Z1 truss. to grapple the P6 truss secured atop the Z1 truss. Parazynski and Tani teamed to disconnect cables Parazynski and Tani teamed to disconnect cables Parazynski and Tani teamed to disconnect cables from the P6, allowing it to be removed from the Z1 from the P6, allowing it to be removed from the Z1 from the P6, allowing it to be removed from the Z1 truss. Tani visually inspected the station’s malfunc- truss. Tani visually inspected the station’s malfunc- truss. Tani visually inspected the station’s malfunc- tioning starboard Solar Alpha Rotary Joint (SARJ) tioning starboard Solar Alpha Rotary Joint (SARJ) tioning starboard Solar Alpha Rotary Joint (SARJ) and gathered samples of “shavings” he found and gathered samples of “shavings” he found and gathered samples of “shavings” he found under the joint’s multilayer insulation covers for under the joint’s multilayer insulation covers for under the joint’s multilayer insulation covers for analysis. EVA 3, 7 hours, 8 minutes; Parazynski and analysis. EVA 3, 7 hours, 8 minutes; Parazynski and analysis. EVA 3, 7 hours, 8 minutes; Parazynski and Wheelock installed the P6 with its set of solar arrays Wheelock installed the P6 with its set of solar arrays Wheelock installed the P6 with its set of solar arrays at its permanent home. As the P6 solar arrays, at its permanent home. As the P6 solar arrays, at its permanent home. As the P6 solar arrays, which had been stowed during previous shuttle which had been stowed during previous shuttle which had been stowed during previous shuttle visits, were deployed, one experienced a tear in visits, were deployed, one experienced a tear in visits, were deployed, one experienced a tear in a blanket as it reached the 80% deployed point. a blanket as it reached the 80% deployed point. a blanket as it reached the 80% deployed point. EVA 4, 7 hours, 19 minutes; Parazynski, riding on EVA 4, 7 hours, 19 minutes; Parazynski, riding on EVA 4, 7 hours, 19 minutes; Parazynski, riding on the station’s robot arm extended by the OBSS, cut the station’s robot arm extended by the OBSS, cut the station’s robot arm extended by the OBSS, cut snagged wires and installed array-stabilizing cuff snagged wires and installed array-stabilizing cuff snagged wires and installed array-stabilizing cuff links designed to strengthen the array’s structures links designed to strengthen the array’s structures links designed to strengthen the array’s structures so it would not tear further. Parazynski took care so it would not tear further. Parazynski took care so it would not tear further. Parazynski took care to keep clear of the swaying array, occasionally to keep clear of the swaying array, occasionally to keep clear of the swaying array, occasionally dampening its motion with a prodder shaped like a dampening its motion with a prodder shaped like a dampening its motion with a prodder shaped like a hockey stick. Wheelock kept watch from the base of hockey stick. Wheelock kept watch from the base of hockey stick. Wheelock kept watch from the base of the solar array to ensure a safe distance was kept the solar array to ensure a safe distance was kept the solar array to ensure a safe distance was kept between Parazynski and the electrically charged between Parazynski and the electrically charged between Parazynski and the electrically charged solar array. After completion of the repairs, the crew solar array. After completion of the repairs, the crew solar array. After completion of the repairs, the crew was able to fully deploy the solar array. was able to fully deploy the solar array. was able to fully deploy the solar array. Of Note: History was made with the meeting in space of Of Note: History was made with the meeting in space of Of Note: History was made with the meeting in space of Peggy Whitson, the first female commander of the Peggy Whitson, the first female commander of the Peggy Whitson, the first female commander of the ISS, and Pam Melroy, the second female com- ISS, and Pam Melroy, the second female com- ISS, and Pam Melroy, the second female com- mander of the space shuttle. mander of the space shuttle. mander of the space shuttle. Parazynski’s use of the Orbiter Boom and Sensor Parazynski’s use of the Orbiter Boom and Sensor Parazynski’s use of the Orbiter Boom and Sensor System (OBSS) during EVA 4 was the first opera- System (OBSS) during EVA 4 was the first opera- System (OBSS) during EVA 4 was the first opera- tional use of the OBSS to reach a worksite. tional use of the OBSS to reach a worksite. tional use of the OBSS to reach a worksite.

Y-106 Y-106 Y-106 STS-122 Mission Facts — Atlantis — STS-122 Mission Facts — Atlantis — STS-122 Mission Facts — Atlantis — Feb. 7–20, 2008 Feb. 7–20, 2008 Feb. 7–20, 2008

Commander: Stephen N. Frick Commander: Stephen N. Frick Commander: Stephen N. Frick Pilot: Alan G. Poindexter Pilot: Alan G. Poindexter Pilot: Alan G. Poindexter Mission Specialist: Rex J. Walheim Mission Specialist: Rex J. Walheim Mission Specialist: Rex J. Walheim Mission Specialist: Stanley G. Love Mission Specialist: Stanley G. Love Mission Specialist: Stanley G. Love Mission Specialist: Leland D. Melvin Mission Specialist: Leland D. Melvin Mission Specialist: Leland D. Melvin Mission Specialist: Hans Schlegel, European Space Mission Specialist: Hans Schlegel, European Space Mission Specialist: Hans Schlegel, European Space Agency (ESA) Agency (ESA) Agency (ESA) ISS Crew Member: Leopold Eyharts, ESA—up only ISS Crew Member: Leopold Eyharts, ESA—up only ISS Crew Member: Leopold Eyharts, ESA—up only ISS Crew Member: Daniel M. Tani—down only ISS Crew Member: Daniel M. Tani—down only ISS Crew Member: Daniel M. Tani—down only Launched: 2:45 p.m. EST, launch pad 39A, Kennedy Launched: 2:45 p.m. EST, launch pad 39A, Kennedy Launched: 2:45 p.m. EST, launch pad 39A, Kennedy Space Center, Fla. Space Center, Fla. Space Center, Fla. Mission Duration: 288 hours (12 days), 18 hours, Mission Duration: 288 hours (12 days), 18 hours, Mission Duration: 288 hours (12 days), 18 hours, 22 minutes 22 minutes 22 minutes Miles Traveled: Approximately 5.3 million statute miles Miles Traveled: Approximately 5.3 million statute miles Miles Traveled: Approximately 5.3 million statute miles Orbits of Earth: 202 Orbits of Earth: 202 Orbits of Earth: 202 Inclination: 51.6 degrees Inclination: 51.6 degrees Inclination: 51.6 degrees Orbital Altitude: 122 nautical miles Orbital Altitude: 122 nautical miles Orbital Altitude: 122 nautical miles Orbital ISS Rendezvous Altitude: Approximately Orbital ISS Rendezvous Altitude: Approximately Orbital ISS Rendezvous Altitude: Approximately 185 nautical miles 185 nautical miles 185 nautical miles Lift-Off Weight: 4,523,252 pounds Lift-Off Weight: 4,523,252 pounds Lift-Off Weight: 4,523,252 pounds Orbiter Weight at Lift-Off: 267,085 pounds Orbiter Weight at Lift-Off: 267,085 pounds Orbiter Weight at Lift-Off: 267,085 pounds Payload Weight Up: 32,941 pounds Payload Weight Up: 32,941 pounds Payload Weight Up: 32,941 pounds Orbiter Weight at Landing: 206,333 pounds Orbiter Weight at Landing: 206,333 pounds Orbiter Weight at Landing: 206,333 pounds Payload Weight Down: 5,800 pounds Payload Weight Down: 5,800 pounds Payload Weight Down: 5,800 pounds Landed: 9:07 a.m. EST, concrete runway 15, Kennedy Landed: 9:07 a.m. EST, concrete runway 15, Kennedy Landed: 9:07 a.m. EST, concrete runway 15, Kennedy Space Center, Fla. Space Center, Fla. Space Center, Fla. Payload: ISS Assembly Flight 1E; Columbus Laboratory; Payload: ISS Assembly Flight 1E; Columbus Laboratory; Payload: ISS Assembly Flight 1E; Columbus Laboratory; crew exchange crew exchange crew exchange Extravehicular Activity (EVA) conducted by Rex Extravehicular Activity (EVA) conducted by Rex Extravehicular Activity (EVA) conducted by Rex Walheim, Stanley Love, and Hans Schlegel. EVA 1, Walheim, Stanley Love, and Hans Schlegel. EVA 1, Walheim, Stanley Love, and Hans Schlegel. EVA 1, 7 hours, 58 minutes; Walheim and Love installed a 7 hours, 58 minutes; Walheim and Love installed a 7 hours, 58 minutes; Walheim and Love installed a grapple fixture on Columbus while it rested inside grapple fixture on Columbus while it rested inside grapple fixture on Columbus while it rested inside the shuttle’s payload bay and prepared electrical the shuttle’s payload bay and prepared electrical the shuttle’s payload bay and prepared electrical and data connections on Columbus. Leland Melvin, and data connections on Columbus. Leland Melvin, and data connections on Columbus. Leland Melvin, Dan Tani, and Leopold Eyharts operated the space Dan Tani, and Leopold Eyharts operated the space Dan Tani, and Leopold Eyharts operated the space station’s robotic arm to grapple Columbus, lift it out station’s robotic arm to grapple Columbus, lift it out station’s robotic arm to grapple Columbus, lift it out of the orbiter, and attach it to the Harmony module of the orbiter, and attach it to the Harmony module of the orbiter, and attach it to the Harmony module on the starboard side of the ISS. EVA 2, 6 hours, on the starboard side of the ISS. EVA 2, 6 hours, on the starboard side of the ISS. EVA 2, 6 hours, 45 minutes; Walheim and Schlegel swapped out a 45 minutes; Walheim and Schlegel swapped out a 45 minutes; Walheim and Schlegel swapped out a 550-lb nitrogen tank used to pressurize ammonia 550-lb nitrogen tank used to pressurize ammonia 550-lb nitrogen tank used to pressurize ammonia through the station’s main cooling system. EVA 3, through the station’s main cooling system. EVA 3, through the station’s main cooling system. EVA 3, 7 hours, 25 minutes; Walheim and Love transferred 7 hours, 25 minutes; Walheim and Love transferred 7 hours, 25 minutes; Walheim and Love transferred a failed gyroscope to the shuttle’s payload bay a failed gyroscope to the shuttle’s payload bay a failed gyroscope to the shuttle’s payload bay for return to Earth, installed an observatory to the for return to Earth, installed an observatory to the for return to Earth, installed an observatory to the Columbus module called SOLAR to monitor the Columbus module called SOLAR to monitor the Columbus module called SOLAR to monitor the sun, and installed an experiment to the outside of sun, and installed an experiment to the outside of sun, and installed an experiment to the outside of Columbus, the European Technology Exposure Columbus, the European Technology Exposure Columbus, the European Technology Exposure Facility (EuTEF). This experiment will allow scientists Facility (EuTEF). This experiment will allow scientists Facility (EuTEF). This experiment will allow scientists to expose experiments to the vacuum and elements to expose experiments to the vacuum and elements to expose experiments to the vacuum and elements of space. of space. of space.

Y-107 Y-107 Y-107 STS-122 Mission Facts (Cont) STS-122 Mission Facts (Cont) STS-122 Mission Facts (Cont)

Of Note: The Columbus Laboratory is Europe’s largest Of Note: The Columbus Laboratory is Europe’s largest Of Note: The Columbus Laboratory is Europe’s largest contribution to the construction of the ISS, adding contribution to the construction of the ISS, adding contribution to the construction of the ISS, adding 2,648 cubic feet of pressurized volume, four science 2,648 cubic feet of pressurized volume, four science 2,648 cubic feet of pressurized volume, four science experiment racks, and one storage rack. With this experiment racks, and one storage rack. With this experiment racks, and one storage rack. With this addition, the station has eight rooms and is now 57 addition, the station has eight rooms and is now 57 addition, the station has eight rooms and is now 57 percent complete in terms of mass. percent complete in terms of mass. percent complete in terms of mass. The landing of Atlantis occurred 46 years to the day The landing of Atlantis occurred 46 years to the day The landing of Atlantis occurred 46 years to the day since Mercury astronaut John Glenn was launched since Mercury astronaut John Glenn was launched since Mercury astronaut John Glenn was launched on an Atlas rocket to become the first American to on an Atlas rocket to become the first American to on an Atlas rocket to become the first American to orbit the Earth. Glenn made just three orbits in his orbit the Earth. Glenn made just three orbits in his orbit the Earth. Glenn made just three orbits in his single-seat Friendship 7 capsule. single-seat Friendship 7 capsule. single-seat Friendship 7 capsule.

STS-123 Mission Facts — Endeavour — STS-123 Mission Facts — Endeavour — STS-123 Mission Facts — Endeavour — March 11–26, 2008 March 11–26, 2008 March 11–26, 2008

Commander: Dominic L. Gorie Commander: Dominic L. Gorie Commander: Dominic L. Gorie Pilot: Gregory H. Johnson Pilot: Gregory H. Johnson Pilot: Gregory H. Johnson Mission Specialist: Richard M. Linnehan Mission Specialist: Richard M. Linnehan Mission Specialist: Richard M. Linnehan Mission Specialist: Robert L. Behnken Mission Specialist: Robert L. Behnken Mission Specialist: Robert L. Behnken Mission Specialist: Michael J. Foreman Mission Specialist: Michael J. Foreman Mission Specialist: Michael J. Foreman Mission Specialist: Takao Doi, Japan Aerospace Mission Specialist: Takao Doi, Japan Aerospace Mission Specialist: Takao Doi, Japan Aerospace Exploration Agency (JAXA) Exploration Agency (JAXA) Exploration Agency (JAXA) ISS Crew Member: Garrett E. Reisman—up only ISS Crew Member: Garrett E. Reisman—up only ISS Crew Member: Garrett E. Reisman—up only ISS Crew Member: Leopold Eyharts, ESA—down only ISS Crew Member: Leopold Eyharts, ESA—down only ISS Crew Member: Leopold Eyharts, ESA—down only Launched: 2:28 a.m. EDT, launch pad 39A, Kennedy Launched: 2:28 a.m. EDT, launch pad 39A, Kennedy Launched: 2:28 a.m. EDT, launch pad 39A, Kennedy Space Center, Fla. Space Center, Fla. Space Center, Fla. Mission Duration: 360 hours (15 days), 18 hours, Mission Duration: 360 hours (15 days), 18 hours, Mission Duration: 360 hours (15 days), 18 hours, 11 minutes 11 minutes 11 minutes Miles Traveled: Approximately 6.6 million statute miles Miles Traveled: Approximately 6.6 million statute miles Miles Traveled: Approximately 6.6 million statute miles Orbits of Earth: 249 Orbits of Earth: 249 Orbits of Earth: 249 Inclination: 51.6 degrees Inclination: 51.6 degrees Inclination: 51.6 degrees Orbital Altitude: 122 nautical miles Orbital Altitude: 122 nautical miles Orbital Altitude: 122 nautical miles Orbital ISS Rendezvous Altitude: Approximately Orbital ISS Rendezvous Altitude: Approximately Orbital ISS Rendezvous Altitude: Approximately 185 nautical miles 185 nautical miles 185 nautical miles Lift-Off Weight: 4,521,086 pounds Lift-Off Weight: 4,521,086 pounds Lift-Off Weight: 4,521,086 pounds Orbiter Weight at Lift-Off: 266,261 pounds Orbiter Weight at Lift-Off: 266,261 pounds Orbiter Weight at Lift-Off: 266,261 pounds Payload Weight Up: 25,839 pounds Payload Weight Up: 25,839 pounds Payload Weight Up: 25,839 pounds Orbiter Weight at Landing: 207,690 pounds Orbiter Weight at Landing: 207,690 pounds Orbiter Weight at Landing: 207,690 pounds Landed: 8:39 p.m. EDT, concrete runway 15, Landed: 8:39 p.m. EDT, concrete runway 15, Landed: 8:39 p.m. EDT, concrete runway 15, Kennedy Space Center, Fla. Kennedy Space Center, Fla. Kennedy Space Center, Fla. Payload: ISS Assembly Flight 1J/A; Kibo Japanese Payload: ISS Assembly Flight 1J/A; Kibo Japanese Payload: ISS Assembly Flight 1J/A; Kibo Japanese Experiment Logistics Module—Pressurized Section Experiment Logistics Module—Pressurized Section Experiment Logistics Module—Pressurized Section (ELM-PS) and Canadian Special Purpose Dexterous (ELM-PS) and Canadian Special Purpose Dexterous (ELM-PS) and Canadian Special Purpose Dexterous Manipulator; crew exchange Manipulator; crew exchange Manipulator; crew exchange Extravehicular Activity (EVA) conducted by Extravehicular Activity (EVA) conducted by Extravehicular Activity (EVA) conducted by Rick Linnehan, Garrett Reisman, Mike Foreman, Rick Linnehan, Garrett Reisman, Mike Foreman, Rick Linnehan, Garrett Reisman, Mike Foreman, and Robert Behnken. EVA 1, 7 hours, 1 minute; and Robert Behnken. EVA 1, 7 hours, 1 minute; and Robert Behnken. EVA 1, 7 hours, 1 minute; Linnehan and Reisman prepared the ELM-PS for Linnehan and Reisman prepared the ELM-PS for Linnehan and Reisman prepared the ELM-PS for removal from the space shuttle payload bay. Takao removal from the space shuttle payload bay. Takao removal from the space shuttle payload bay. Takao Doi used Canadarm to move the ELM-PS to its Doi used Canadarm to move the ELM-PS to its Doi used Canadarm to move the ELM-PS to its interim location on the zenith port of Harmony. The interim location on the zenith port of Harmony. The interim location on the zenith port of Harmony. The ELM-PS will be relocated to its permanent location ELM-PS will be relocated to its permanent location ELM-PS will be relocated to its permanent location

Y-108 Y-108 Y-108 STS-123 Mission Facts (Cont) STS-123 Mission Facts (Cont) STS-123 Mission Facts (Cont)

after the arrival of the Pressurized Module on space after the arrival of the Pressurized Module on space after the arrival of the Pressurized Module on space shuttle mission STS-124. Linnehan and Reisman shuttle mission STS-124. Linnehan and Reisman shuttle mission STS-124. Linnehan and Reisman also worked on the initial assembly of the Special also worked on the initial assembly of the Special also worked on the initial assembly of the Special Purpose Dexterous Manipulator, also known as Purpose Dexterous Manipulator, also known as Purpose Dexterous Manipulator, also known as “Dextre,” installing both orbital replacement unit/tool “Dextre,” installing both orbital replacement unit/tool “Dextre,” installing both orbital replacement unit/tool changeout mechanisms (OTCMs), the “hands” of changeout mechanisms (OTCMs), the “hands” of changeout mechanisms (OTCMs), the “hands” of Dextre’s arms. EVA 2, 7 hours, 8 minutes; Dextre’s arms. EVA 2, 7 hours, 8 minutes; Dextre’s arms. EVA 2, 7 hours, 8 minutes; Linnehan and Foreman attached the two arms Linnehan and Foreman attached the two arms Linnehan and Foreman attached the two arms of Dextre. EVA 3, 6 hours, 53 minutes; Linnehan of Dextre. EVA 3, 6 hours, 53 minutes; Linnehan of Dextre. EVA 3, 6 hours, 53 minutes; Linnehan and Behnken finished assembly and installation of and Behnken finished assembly and installation of and Behnken finished assembly and installation of Dextre. EVA 4, 6 hours, 24 minutes; the major focus Dextre. EVA 4, 6 hours, 24 minutes; the major focus Dextre. EVA 4, 6 hours, 24 minutes; the major focus of this spacewalk by Behnken and Foreman was a of this spacewalk by Behnken and Foreman was a of this spacewalk by Behnken and Foreman was a demonstration of the Tile Repair Ablator Dispenser, demonstration of the Tile Repair Ablator Dispenser, demonstration of the Tile Repair Ablator Dispenser, a caulk gun-like device. A substance called Shuttle a caulk gun-like device. A substance called Shuttle a caulk gun-like device. A substance called Shuttle Tile Ablator-54 (STA-54) was applied to intention- Tile Ablator-54 (STA-54) was applied to intention- Tile Ablator-54 (STA-54) was applied to intention- ally damaged heat shield tiles, which were returned ally damaged heat shield tiles, which were returned ally damaged heat shield tiles, which were returned to Earth for testing to determine how STA-54 to Earth for testing to determine how STA-54 to Earth for testing to determine how STA-54 performed in both a microgravity and vacuum envi- performed in both a microgravity and vacuum envi- performed in both a microgravity and vacuum envi- ronment. EVA 5, 6 hours, 2 minutes; Behnken and ronment. EVA 5, 6 hours, 2 minutes; Behnken and ronment. EVA 5, 6 hours, 2 minutes; Behnken and Foreman installed the Materials International Space Foreman installed the Materials International Space Foreman installed the Materials International Space Station Experiment–6 (MISSE-6) and inspected the Station Experiment–6 (MISSE-6) and inspected the Station Experiment–6 (MISSE-6) and inspected the station’s right Solar Alpha Rotary Joint, where metal station’s right Solar Alpha Rotary Joint, where metal station’s right Solar Alpha Rotary Joint, where metal shavings had previously been discovered. shavings had previously been discovered. shavings had previously been discovered. Of Note: A record five spacewalks were conducted dur- Of Note: A record five spacewalks were conducted dur- Of Note: A record five spacewalks were conducted dur- ing STS-123, also the longest mission to date at the ing STS-123, also the longest mission to date at the ing STS-123, also the longest mission to date at the ISS. ISS. ISS. Because the Kibo Japanese Experiment Module– Because the Kibo Japanese Experiment Module– Because the Kibo Japanese Experiment Module– Pressurized Module (JEM–PM) that will be launched Pressurized Module (JEM–PM) that will be launched Pressurized Module (JEM–PM) that will be launched on mission STS-124 is so large, the shuttle’s Orbiter on mission STS-124 is so large, the shuttle’s Orbiter on mission STS-124 is so large, the shuttle’s Orbiter Boom Sensor System (OBSS), the extension of the Boom Sensor System (OBSS), the extension of the Boom Sensor System (OBSS), the extension of the Canadarm that is usually carried in the shuttle’s Canadarm that is usually carried in the shuttle’s Canadarm that is usually carried in the shuttle’s cargo bay, was removed and stowed on the ISS. cargo bay, was removed and stowed on the ISS. cargo bay, was removed and stowed on the ISS. The OBSS will be returned to Earth at the end of the The OBSS will be returned to Earth at the end of the The OBSS will be returned to Earth at the end of the next shuttle mission. next shuttle mission. next shuttle mission.

STS-124 Mission Facts — Discovery — STS-124 Mission Facts — Discovery — STS-124 Mission Facts — Discovery — May 31–June 14, 2008 May 31–June 14, 2008 May 31–June 14, 2008 Commander: Mark E. Kelly Commander: Mark E. Kelly Commander: Mark E. Kelly Pilot: Kenneth T. Ham Pilot: Kenneth T. Ham Pilot: Kenneth T. Ham Mission Specialist: Karen L. Nyberg Mission Specialist: Karen L. Nyberg Mission Specialist: Karen L. Nyberg Mission Specialist: Ronald J. Garan Mission Specialist: Ronald J. Garan Mission Specialist: Ronald J. Garan Mission Specialist: Michael E. Fossum Mission Specialist: Michael E. Fossum Mission Specialist: Michael E. Fossum Mission Specialist: Akihiko Hoshide, Japan Aerospace Mission Specialist: Akihiko Hoshide, Japan Aerospace Mission Specialist: Akihiko Hoshide, Japan Aerospace Exploration Agency (JAXA) Exploration Agency (JAXA) Exploration Agency (JAXA) ISS Crew Member: Gregory E. Chamitoff—up only ISS Crew Member: Gregory E. Chamitoff—up only ISS Crew Member: Gregory E. Chamitoff—up only ISS Crew Member: Garrett E. Reisman—down only ISS Crew Member: Garrett E. Reisman—down only ISS Crew Member: Garrett E. Reisman—down only Launched: 5:02 p.m. EDT, launch pad 39A, Kennedy Launched: 5:02 p.m. EDT, launch pad 39A, Kennedy Launched: 5:02 p.m. EDT, launch pad 39A, Kennedy Space Center, Fla. Space Center, Fla. Space Center, Fla. Mission Duration: 312 hours (13 days), 18 hours, Mission Duration: 312 hours (13 days), 18 hours, Mission Duration: 312 hours (13 days), 18 hours, 13 minutes 13 minutes 13 minutes Miles Traveled: Approximately 5.7 million statute miles Miles Traveled: Approximately 5.7 million statute miles Miles Traveled: Approximately 5.7 million statute miles

Y-109 Y-109 Y-109 STS-124 Mission Facts (Cont) STS-124 Mission Facts (Cont) STS-124 Mission Facts (Cont)

Orbits of Earth: 217 Orbits of Earth: 217 Orbits of Earth: 217 Inclination: 51.6 degrees Inclination: 51.6 degrees Inclination: 51.6 degrees Orbital Altitude: 122 nautical miles Orbital Altitude: 122 nautical miles Orbital Altitude: 122 nautical miles Orbital ISS Rendezvous Altitude: Approximately Orbital ISS Rendezvous Altitude: Approximately Orbital ISS Rendezvous Altitude: Approximately 185 nautical miles 185 nautical miles 185 nautical miles Lift-Off Weight: 4,525,084 pounds Lift-Off Weight: 4,525,084 pounds Lift-Off Weight: 4,525,084 pounds Orbiter Weight at Lift-Off: 269,123 pounds Orbiter Weight at Lift-Off: 269,123 pounds Orbiter Weight at Lift-Off: 269,123 pounds Payload Weight Up: 33,969 pounds Payload Weight Up: 33,969 pounds Payload Weight Up: 33,969 pounds Orbiter Weight at Landing: 203,320 pounds Orbiter Weight at Landing: 203,320 pounds Orbiter Weight at Landing: 203,320 pounds Payload Weight Down: 1,687 pounds Payload Weight Down: 1,687 pounds Payload Weight Down: 1,687 pounds Landed: 11:15 a.m. EDT, concrete runway 15, Landed: 11:15 a.m. EDT, concrete runway 15, Landed: 11:15 a.m. EDT, concrete runway 15, Kennedy Space Center, Fla. Kennedy Space Center, Fla. Kennedy Space Center, Fla. Payload: ISS Assembly Flight 1J; Japanese Experiment Payload: ISS Assembly Flight 1J; Japanese Experiment Payload: ISS Assembly Flight 1J; Japanese Experiment Module–Pressurized Module (JEM-PM) and Japa- Module–Pressurized Module (JEM-PM) and Japa- Module–Pressurized Module (JEM-PM) and Japa- nese Remote Manipulator System; crew exchange nese Remote Manipulator System; crew exchange nese Remote Manipulator System; crew exchange Extravehicular Activity (EVA) conducted by Mike Fos- Extravehicular Activity (EVA) conducted by Mike Fos- Extravehicular Activity (EVA) conducted by Mike Fos- sum and Ron Garan. EVA 1, 6 hours, 48 minutes; sum and Ron Garan. EVA 1, 6 hours, 48 minutes; sum and Ron Garan. EVA 1, 6 hours, 48 minutes; Fossum and Garan prepared the Kibo JEM-PM for Fossum and Garan prepared the Kibo JEM-PM for Fossum and Garan prepared the Kibo JEM-PM for installation on the ISS by disconnecting cables and installation on the ISS by disconnecting cables and installation on the ISS by disconnecting cables and removing covers while Kibo was still in the shuttle’s removing covers while Kibo was still in the shuttle’s removing covers while Kibo was still in the shuttle’s payload bay. They also assisted with the transfer payload bay. They also assisted with the transfer payload bay. They also assisted with the transfer of the Orbiter Boom Sensor System (OBSS) back of the Orbiter Boom Sensor System (OBSS) back of the Orbiter Boom Sensor System (OBSS) back to the shuttle from the station, where it had been to the shuttle from the station, where it had been to the shuttle from the station, where it had been stored since the last shuttle visit. EVA 2, 7 hours, stored since the last shuttle visit. EVA 2, 7 hours, stored since the last shuttle visit. EVA 2, 7 hours, 11 minutes; Fossum and Garan focused on external 11 minutes; Fossum and Garan focused on external 11 minutes; Fossum and Garan focused on external outfitting of the new module, including installing outfitting of the new module, including installing outfitting of the new module, including installing cameras that will help monitor external robotic and cameras that will help monitor external robotic and cameras that will help monitor external robotic and payload operations. EVA 3, 6 hours, 33 minutes; payload operations. EVA 3, 6 hours, 33 minutes; payload operations. EVA 3, 6 hours, 33 minutes; Fossum and Garan replaced a nitrogen tank as- Fossum and Garan replaced a nitrogen tank as- Fossum and Garan replaced a nitrogen tank as- sembly (NTA) on the station’s starboard truss. After sembly (NTA) on the station’s starboard truss. After sembly (NTA) on the station’s starboard truss. After they detached the empty NTA, Garan rode the fully they detached the empty NTA, Garan rode the fully they detached the empty NTA, Garan rode the fully extended Canadarm2 from the tank’s installation extended Canadarm2 from the tank’s installation extended Canadarm2 from the tank’s installation area to External Storage Platform-3, where it will be area to External Storage Platform-3, where it will be area to External Storage Platform-3, where it will be stored until its return on the STS-126 mission. stored until its return on the STS-126 mission. stored until its return on the STS-126 mission. Of Note: Karen Nyberg became the 50th woman in space Of Note: Karen Nyberg became the 50th woman in space Of Note: Karen Nyberg became the 50th woman in space and the first person to operate three robot arms— and the first person to operate three robot arms— and the first person to operate three robot arms— the station arm, the shuttle arm, and the Kibo arm. the station arm, the shuttle arm, and the Kibo arm. the station arm, the shuttle arm, and the Kibo arm. She and Akihiko Hoshide used the station’s arm to She and Akihiko Hoshide used the station’s arm to She and Akihiko Hoshide used the station’s arm to remove the JEM-PM from Discovery’s payload bay remove the JEM-PM from Discovery’s payload bay remove the JEM-PM from Discovery’s payload bay and latch it in place on the port side of the Harmony and latch it in place on the port side of the Harmony and latch it in place on the port side of the Harmony node. She and Greg Chamitoff later used the node. She and Greg Chamitoff later used the node. She and Greg Chamitoff later used the station’s arm to relocate the Japanese Experiment station’s arm to relocate the Japanese Experiment station’s arm to relocate the Japanese Experiment Logistics Module–Pressurized Section (ELM-PS) to Logistics Module–Pressurized Section (ELM-PS) to Logistics Module–Pressurized Section (ELM-PS) to its permanent home on top of the newly installed its permanent home on top of the newly installed its permanent home on top of the newly installed JEM-PM. Kibo’s JEM-PM is the largest shuttle pay- JEM-PM. Kibo’s JEM-PM is the largest shuttle pay- JEM-PM. Kibo’s JEM-PM is the largest shuttle pay- load delivered to the station to date and is now the load delivered to the station to date and is now the load delivered to the station to date and is now the largest pressurized module on the ISS. largest pressurized module on the ISS. largest pressurized module on the ISS. STS-124 also marked the first time the JAXA flight STS-124 also marked the first time the JAXA flight STS-124 also marked the first time the JAXA flight control team activated and controlled a module control team activated and controlled a module control team activated and controlled a module from Kibo Mission Control in Tsukuba, Japan. from Kibo Mission Control in Tsukuba, Japan. from Kibo Mission Control in Tsukuba, Japan.

Y-110 Y-110 Y-110 STS-126 Mission Facts — Endeavour — STS-126 Mission Facts — Endeavour — STS-126 Mission Facts — Endeavour — Nov. 14–30, 2008 Nov. 14–30, 2008 Nov. 14–30, 2008

Commander: Christopher J. Ferguson Commander: Christopher J. Ferguson Commander: Christopher J. Ferguson Pilot: Eric A. Boe Pilot: Eric A. Boe Pilot: Eric A. Boe Mission Specialist: Stephen G. Bowen Mission Specialist: Stephen G. Bowen Mission Specialist: Stephen G. Bowen Mission Specialist: Donald R. Pettit Mission Specialist: Donald R. Pettit Mission Specialist: Donald R. Pettit Mission Specialist: Robert S. Kimbrough Mission Specialist: Robert S. Kimbrough Mission Specialist: Robert S. Kimbrough Mission Specialist: Heidemarie M. Stefanyshyn-Piper Mission Specialist: Heidemarie M. Stefanyshyn-Piper Mission Specialist: Heidemarie M. Stefanyshyn-Piper ISS Crew Member: Sandra H. Magnus—up only ISS Crew Member: Sandra H. Magnus—up only ISS Crew Member: Sandra H. Magnus—up only ISS Crew Member: Gregory Chamitoff—down only ISS Crew Member: Gregory Chamitoff—down only ISS Crew Member: Gregory Chamitoff—down only Launched: 7:55 p.m. EST, launch pad 39A, Kennedy Launched: 7:55 p.m. EST, launch pad 39A, Kennedy Launched: 7:55 p.m. EST, launch pad 39A, Kennedy Space Center, Fla. Space Center, Fla. Space Center, Fla. Mission Duration: 360 hours (15 days), 20 hours, Mission Duration: 360 hours (15 days), 20 hours, Mission Duration: 360 hours (15 days), 20 hours, 30 minutes 30 minutes 30 minutes Miles Traveled: 6,615,109 statute miles Miles Traveled: 6,615,109 statute miles Miles Traveled: 6,615,109 statute miles Orbits of Earth: 251 Orbits of Earth: 251 Orbits of Earth: 251 Inclination: 51.6 degrees Inclination: 51.6 degrees Inclination: 51.6 degrees Orbital Altitude: 122 nautical miles Orbital Altitude: 122 nautical miles Orbital Altitude: 122 nautical miles Orbital ISS Rendezvous Altitude: Approximately 190 Orbital ISS Rendezvous Altitude: Approximately 190 Orbital ISS Rendezvous Altitude: Approximately 190 nautical miles nautical miles nautical miles Lift-Off Weight: 4,523,242 pounds Lift-Off Weight: 4,523,242 pounds Lift-Off Weight: 4,523,242 pounds Orbiter Weight at Lift-Off: 267,014 pounds Orbiter Weight at Lift-Off: 267,014 pounds Orbiter Weight at Lift-Off: 267,014 pounds Payload Weight Up: 39,501 pounds Payload Weight Up: 39,501 pounds Payload Weight Up: 39,501 pounds Orbiter Weight at Landing: 221,336 pounds Orbiter Weight at Landing: 221,336 pounds Orbiter Weight at Landing: 221,336 pounds Payload Weight Down: 22,845 pounds Payload Weight Down: 22,845 pounds Payload Weight Down: 22,845 pounds Landed: 4:25 p.m. EST, Edwards Air Force Base, Calif. Landed: 4:25 p.m. EST, Edwards Air Force Base, Calif. Landed: 4:25 p.m. EST, Edwards Air Force Base, Calif. Payload: ISS Assembly Flight ULF2; Leonardo Multi- Payload: ISS Assembly Flight ULF2; Leonardo Multi- Payload: ISS Assembly Flight ULF2; Leonardo Multi- Purpose Logistics Module; crew exchange Purpose Logistics Module; crew exchange Purpose Logistics Module; crew exchange Extravehicular Activity (EVA) conducted by Heidemarie Extravehicular Activity (EVA) conducted by Heidemarie Extravehicular Activity (EVA) conducted by Heidemarie Stefanyshyn-Piper, Stephen Bowen, and Robert Stefanyshyn-Piper, Stephen Bowen, and Robert Stefanyshyn-Piper, Stephen Bowen, and Robert Kimbrough. EVA 1, 6 hours, 52 minutes; Piper and Kimbrough. EVA 1, 6 hours, 52 minutes; Piper and Kimbrough. EVA 1, 6 hours, 52 minutes; Piper and Bowen spent the majority of this spacewalk focus- Bowen spent the majority of this spacewalk focus- Bowen spent the majority of this spacewalk focus- ing on one of the station’s starboard Solar Alpha ing on one of the station’s starboard Solar Alpha ing on one of the station’s starboard Solar Alpha Rotary Joints (SARJ). These joints are the large, Rotary Joints (SARJ). These joints are the large, Rotary Joints (SARJ). These joints are the large, circular devices that allow the complex’s solar ar- circular devices that allow the complex’s solar ar- circular devices that allow the complex’s solar ar- rays to automatically rotate and track the sun as the rays to automatically rotate and track the sun as the rays to automatically rotate and track the sun as the station orbits the Earth. Piper and Bowen cleaned station orbits the Earth. Piper and Bowen cleaned station orbits the Earth. Piper and Bowen cleaned and lubricated part of the joint and removed two and lubricated part of the joint and removed two and lubricated part of the joint and removed two of the joint’s 12 trundle bearing assemblies (TBA). of the joint’s 12 trundle bearing assemblies (TBA). of the joint’s 12 trundle bearing assemblies (TBA). They also replaced a depleted nitrogen tank on a They also replaced a depleted nitrogen tank on a They also replaced a depleted nitrogen tank on a stowage platform outside the ISS. Additionally, they stowage platform outside the ISS. Additionally, they stowage platform outside the ISS. Additionally, they removed some insulation blankets from the com- removed some insulation blankets from the com- removed some insulation blankets from the com- mon berthing mechanism on the Kibo laboratory. mon berthing mechanism on the Kibo laboratory. mon berthing mechanism on the Kibo laboratory. EVA 2, 6 hours, 45 minutes; Piper and Kimbrough EVA 2, 6 hours, 45 minutes; Piper and Kimbrough EVA 2, 6 hours, 45 minutes; Piper and Kimbrough continued to remove debris around the SARJ and continued to remove debris around the SARJ and continued to remove debris around the SARJ and apply lubrication, as well as replaced four more of apply lubrication, as well as replaced four more of apply lubrication, as well as replaced four more of the 12 TBAs. They also relocated two equipment the 12 TBAs. They also relocated two equipment the 12 TBAs. They also relocated two equipment carts in preparation for the installation of the final carts in preparation for the installation of the final carts in preparation for the installation of the final pair of solar arrays during space shuttle mission pair of solar arrays during space shuttle mission pair of solar arrays during space shuttle mission STS-119. EVA 3, 6 hours, 57 minutes; Piper and STS-119. EVA 3, 6 hours, 57 minutes; Piper and STS-119. EVA 3, 6 hours, 57 minutes; Piper and

Y-111 Y-111 Y-111 STS-126 Mission Facts (Cont) STS-126 Mission Facts (Cont) STS-126 Mission Facts (Cont)

Bowen continued cleaning the starboard SARJ Bowen continued cleaning the starboard SARJ Bowen continued cleaning the starboard SARJ and replaced additional TBAs. EVA 4, 6 hours, and replaced additional TBAs. EVA 4, 6 hours, and replaced additional TBAs. EVA 4, 6 hours, 7 minutes; Bowen and Kimbrough installed the final 7 minutes; Bowen and Kimbrough installed the final 7 minutes; Bowen and Kimbrough installed the final TBA on the starboard SARJ and added lubrication TBA on the starboard SARJ and added lubrication TBA on the starboard SARJ and added lubrication to the port SARJ. They also retracted a berthing to the port SARJ. They also retracted a berthing to the port SARJ. They also retracted a berthing mechanism latch on the Kibo lab and reinstalled its mechanism latch on the Kibo lab and reinstalled its mechanism latch on the Kibo lab and reinstalled its thermal cover. thermal cover. thermal cover. Of Note: Endeavour delivered equipment that will Of Note: Endeavour delivered equipment that will Of Note: Endeavour delivered equipment that will allow the station to double its crew size to six. The allow the station to double its crew size to six. The allow the station to double its crew size to six. The gear included two sleep stations, a new galley, a gear included two sleep stations, a new galley, a gear included two sleep stations, a new galley, a second bathroom, an advanced resistive exercise second bathroom, an advanced resistive exercise second bathroom, an advanced resistive exercise device, and a water recovery system that will allow device, and a water recovery system that will allow device, and a water recovery system that will allow urine and other condensate to be purified and urine and other condensate to be purified and urine and other condensate to be purified and converted into water for the crew’s use. converted into water for the crew’s use. converted into water for the crew’s use.

Endeavour launched with the heaviest MPLM pay- Endeavour launched with the heaviest MPLM pay- Endeavour launched with the heaviest MPLM pay- load to date, carrying more than 1,000 items for the load to date, carrying more than 1,000 items for the load to date, carrying more than 1,000 items for the ISS. Because of the heavy payload, the MPLM was ISS. Because of the heavy payload, the MPLM was ISS. Because of the heavy payload, the MPLM was redesigned by Thales Alenia Space to enable it to redesigned by Thales Alenia Space to enable it to redesigned by Thales Alenia Space to enable it to carry an extra 600 pounds. carry an extra 600 pounds. carry an extra 600 pounds.

During this mission, the ISS celebrated the 10th an- During this mission, the ISS celebrated the 10th an- During this mission, the ISS celebrated the 10th an- niversary since its construction began on Nov. 20, niversary since its construction began on Nov. 20, niversary since its construction began on Nov. 20, 1998, with the launch of the Zarya module. 1998, with the launch of the Zarya module. 1998, with the launch of the Zarya module.

STS-119 Mission Facts — Discovery — STS-119 Mission Facts — Discovery — STS-119 Mission Facts — Discovery — March 15–28, 2009 March 15–28, 2009 March 15–28, 2009

Commander: Lee J. Archambault Commander: Lee J. Archambault Commander: Lee J. Archambault Pilot: Dominic A. Antonelli Pilot: Dominic A. Antonelli Pilot: Dominic A. Antonelli Mission Specialist/Educator Astronaut: Joseph M. Acaba Mission Specialist/Educator Astronaut: Joseph M. Acaba Mission Specialist/Educator Astronaut: Joseph M. Acaba Mission Specialist: Steven R. Swanson Mission Specialist: Steven R. Swanson Mission Specialist: Steven R. Swanson Mission Specialist/Educator Astronaut: Richard R. Arnold II Mission Specialist/Educator Astronaut: Richard R. Arnold II Mission Specialist/Educator Astronaut: Richard R. Arnold II Mission Specialist: John L. Phillips Mission Specialist: John L. Phillips Mission Specialist: John L. Phillips ISS Crew Member: Koichi Wakata—up only ISS Crew Member: Koichi Wakata—up only ISS Crew Member: Koichi Wakata—up only ISS Crew Member: Sandra H. Magnus—down only ISS Crew Member: Sandra H. Magnus—down only ISS Crew Member: Sandra H. Magnus—down only Launched: 7:43 p.m. EDT, launch pad 39A, Kennedy Launched: 7:43 p.m. EDT, launch pad 39A, Kennedy Launched: 7:43 p.m. EDT, launch pad 39A, Kennedy Space Center, Fla. Space Center, Fla. Space Center, Fla. Mission Duration: 288 hours (12 days), 19 hours, Mission Duration: 288 hours (12 days), 19 hours, Mission Duration: 288 hours (12 days), 19 hours, 30 minutes 30 minutes 30 minutes Miles Traveled: 5,304,140 statute miles Miles Traveled: 5,304,140 statute miles Miles Traveled: 5,304,140 statute miles Orbits of Earth: 202 Orbits of Earth: 202 Orbits of Earth: 202 Inclination: 51.6 degrees Inclination: 51.6 degrees Inclination: 51.6 degrees Orbital Altitude: 122 nautical miles Orbital Altitude: 122 nautical miles Orbital Altitude: 122 nautical miles Orbital ISS Rendezvous Altitude: Approximately 195 Orbital ISS Rendezvous Altitude: Approximately 195 Orbital ISS Rendezvous Altitude: Approximately 195 nautical miles nautical miles nautical miles Lift-Off Weight: 4,521,897 pounds Lift-Off Weight: 4,521,897 pounds Lift-Off Weight: 4,521,897 pounds Orbiter Weight at Lift-Off: 266,448 pounds Orbiter Weight at Lift-Off: 266,448 pounds Orbiter Weight at Lift-Off: 266,448 pounds Payload Weight Up: 32,546 pounds Payload Weight Up: 32,546 pounds Payload Weight Up: 32,546 pounds Orbiter Weight at Landing: 200,986 pounds Orbiter Weight at Landing: 200,986 pounds Orbiter Weight at Landing: 200,986 pounds Payload Weight Down: 1,963 pounds

Y-112 Y-112 Y-112 STS-119 Mission Facts (Cont) STS-119 Mission Facts (Cont) STS-119 Mission Facts (Cont)

Landed: 3:15 p.m. EDT, concrete runway 15, Kennedy Landed: 3:15 p.m. EDT, concrete runway 15, Kennedy Landed: 3:15 p.m. EDT, concrete runway 15, Kennedy Space Center, Fla. Space Center, Fla. Space Center, Fla. Payload: ISS Assembly Flight 15A; ITS S6, fourth star- Payload: ISS Assembly Flight 15A; ITS S6, fourth star- Payload: ISS Assembly Flight 15A; ITS S6, fourth star- board truss segment; fourth set of solar arrays and board truss segment; fourth set of solar arrays and board truss segment; fourth set of solar arrays and batteries; replacement distillation assembly for ISS batteries; replacement distillation assembly for ISS batteries; replacement distillation assembly for ISS water recycling system; crew exchange water recycling system; crew exchange water recycling system; crew exchange Extravehicular Activity (EVA) conducted by Steven Extravehicular Activity (EVA) conducted by Steven Extravehicular Activity (EVA) conducted by Steven Swanson, Richard Arnold, and Joseph Acaba. Swanson, Richard Arnold, and Joseph Acaba. Swanson, Richard Arnold, and Joseph Acaba. EVA 1, 6 hours, 7 minutes; Phillips and Magnus had EVA 1, 6 hours, 7 minutes; Phillips and Magnus had EVA 1, 6 hours, 7 minutes; Phillips and Magnus had previously used Canadarm2 to grapple S6, remove previously used Canadarm2 to grapple S6, remove previously used Canadarm2 to grapple S6, remove it from the shuttle payload bay, and position the it from the shuttle payload bay, and position the it from the shuttle payload bay, and position the S6 near the outboard end of the starboard truss. S6 near the outboard end of the starboard truss. S6 near the outboard end of the starboard truss. Swanson and Arnold then provided guidance to Swanson and Arnold then provided guidance to Swanson and Arnold then provided guidance to Phillips and Wakata for the final positioning of the Phillips and Wakata for the final positioning of the Phillips and Wakata for the final positioning of the S6 using Canadarm2, installed the S6 truss to the S6 using Canadarm2, installed the S6 truss to the S6 using Canadarm2, installed the S6 truss to the S5 truss, connected S5/S6 umbilicals, released S5 truss, connected S5/S6 umbilicals, released S5 truss, connected S5/S6 umbilicals, released launch restraints, removed keel pins, stored and launch restraints, removed keel pins, stored and launch restraints, removed keel pins, stored and removed thermal covers, and deployed the S6 removed thermal covers, and deployed the S6 removed thermal covers, and deployed the S6 photovoltaic radiator. EVA 2, 6 hours, 30 minutes; photovoltaic radiator. EVA 2, 6 hours, 30 minutes; photovoltaic radiator. EVA 2, 6 hours, 30 minutes; Swanson and Acaba performed advanced prepara- Swanson and Acaba performed advanced prepara- Swanson and Acaba performed advanced prepara- tion of a worksite for STS-127, completed partial tion of a worksite for STS-127, completed partial tion of a worksite for STS-127, completed partial installation of an unpressurized cargo carrier attach- installation of an unpressurized cargo carrier attach- installation of an unpressurized cargo carrier attach- ment system on the P3 truss, and installed a Global ment system on the P3 truss, and installed a Global ment system on the P3 truss, and installed a Global Positioning System antenna to the Kibo laboratory. Positioning System antenna to the Kibo laboratory. Positioning System antenna to the Kibo laboratory. EVA 3, 6 hours, 27 minutes; Arnold and Acaba EVA 3, 6 hours, 27 minutes; Arnold and Acaba EVA 3, 6 hours, 27 minutes; Arnold and Acaba relocated a crew equipment cart, lubricated station relocated a crew equipment cart, lubricated station relocated a crew equipment cart, lubricated station arm grapple snares, and attempted deployment of arm grapple snares, and attempted deployment of arm grapple snares, and attempted deployment of a cargo carrier. a cargo carrier. a cargo carrier. Of Note: With the installation of S6, the 335-foot-long Of Note: With the installation of S6, the 335-foot-long Of Note: With the installation of S6, the 335-foot-long truss is complete, and the ISS is 81 percent com- truss is complete, and the ISS is 81 percent com- truss is complete, and the ISS is 81 percent com- plete. The four pairs of solar arrays have a total plete. The four pairs of solar arrays have a total plete. The four pairs of solar arrays have a total surface area of 38,400 square feet, or 0.9 acre. surface area of 38,400 square feet, or 0.9 acre. surface area of 38,400 square feet, or 0.9 acre. The arrays now produce 120 kilowatts of usable The arrays now produce 120 kilowatts of usable The arrays now produce 120 kilowatts of usable electricity, doubling the previous amount available electricity, doubling the previous amount available electricity, doubling the previous amount available for science operations to 30 kilowatts. for science operations to 30 kilowatts. for science operations to 30 kilowatts.

STS-125 Mission Facts — Atlantis — STS-125 Mission Facts — Atlantis — STS-125 Mission Facts — Atlantis — May 11–24, 2009 May 11–24, 2009 May 11–24, 2009

Commander: Scott D. Altman Commander: Scott D. Altman Commander: Scott D. Altman Pilot: Gregory C. Johnson Pilot: Gregory C. Johnson Pilot: Gregory C. Johnson Mission Specialist: Andrew J. Feustel Mission Specialist: Andrew J. Feustel Mission Specialist: Andrew J. Feustel Mission Specialist: Michael T. Good Mission Specialist: Michael T. Good Mission Specialist: Michael T. Good Mission Specialist: John M. Grunsfeld Mission Specialist: John M. Grunsfeld Mission Specialist: John M. Grunsfeld Mission Specialist: Michael J. Massimino Mission Specialist: Michael J. Massimino Mission Specialist: Michael J. Massimino Mission Specialist: K. Megan McArthur Mission Specialist: K. Megan McArthur Mission Specialist: K. Megan McArthur Launched: 2:01 p.m. EDT, launch pad 39A, Kennedy Launched: 2:01 p.m. EDT, launch pad 39A, Kennedy Launched: 2:01 p.m. EDT, launch pad 39A, Kennedy Space Center, Fla. Space Center, Fla. Space Center, Fla. Mission Duration: 288 hours (12 days), 21 hours, Mission Duration: 288 hours (12 days), 21 hours, Mission Duration: 288 hours (12 days), 21 hours, 37 minutes 37 minutes 37 minutes Miles Traveled: 5,276,000 statute miles Miles Traveled: 5,276,000 statute miles Miles Traveled: 5,276,000 statute miles Orbits of Earth: 197 Orbits of Earth: 197 Orbits of Earth: 197

Y-113 Y-113 Y-113 STS-125 Mission Facts (Cont) STS-125 Mission Facts (Cont) STS-125 Mission Facts (Cont)

Inclination: 28.5 degrees Inclination: 28.5 degrees Inclination: 28.5 degrees Orbital Altitude: 297 nautical miles Orbital Altitude: 297 nautical miles Orbital Altitude: 297 nautical miles Lift-Off Weight: 4,519,343 pounds Lift-Off Weight: 4,519,343 pounds Lift-Off Weight: 4,519,343 pounds Orbiter Weight at Lift-Off: 264,165 pounds Orbiter Weight at Lift-Off: 264,165 pounds Orbiter Weight at Lift-Off: 264,165 pounds Payload Weight Up: 22,254 pounds Payload Weight Up: 22,254 pounds Payload Weight Up: 22,254 pounds Orbiter Weight at Landing: 226,040 pounds Orbiter Weight at Landing: 226,040 pounds Orbiter Weight at Landing: 226,040 pounds Payload Weight Down: 21,453 pounds Payload Weight Down: 21,453 pounds Payload Weight Down: 21,453 pounds Landed: 11:39 a.m. EDT, concrete runway 22, Edwards Landed: 11:39 a.m. EDT, concrete runway 22, Edwards Landed: 11:39 a.m. EDT, concrete runway 22, Edwards Air Force Base, Calif. Air Force Base, Calif. Air Force Base, Calif. Payload: Hubble Space Telescope Servicing Mission 4 Payload: Hubble Space Telescope Servicing Mission 4 Payload: Hubble Space Telescope Servicing Mission 4 to repair and refurbish the orbiting observatory's to repair and refurbish the orbiting observatory's to repair and refurbish the orbiting observatory's capabilities capabilities capabilities Extravehicular Activity (EVA) conducted by team of John Extravehicular Activity (EVA) conducted by team of John Extravehicular Activity (EVA) conducted by team of John Grunsfeld and Andrew Feustel and team of Michael Grunsfeld and Andrew Feustel and team of Michael Grunsfeld and Andrew Feustel and team of Michael Good and Michael Massimino during five back-to- Good and Michael Massimino during five back-to- Good and Michael Massimino during five back-to- back spacewalks for a total of 36 hours, 56 minutes. back spacewalks for a total of 36 hours, 56 minutes. back spacewalks for a total of 36 hours, 56 minutes. Megan McArthur used the Canadarm to grapple Megan McArthur used the Canadarm to grapple Megan McArthur used the Canadarm to grapple Hubble, maneuver it onto a flight support system Hubble, maneuver it onto a flight support system Hubble, maneuver it onto a flight support system maintenance platform in the shuttle’s payload bay, maintenance platform in the shuttle’s payload bay, maintenance platform in the shuttle’s payload bay, and subsequently to release Hubble when the and subsequently to release Hubble when the and subsequently to release Hubble when the repairs were complete. EVA 1, 7 hours, 20 minutes; repairs were complete. EVA 1, 7 hours, 20 minutes; repairs were complete. EVA 1, 7 hours, 20 minutes; Grunsfeld and Feustel removed Wide-Field and Grunsfeld and Feustel removed Wide-Field and Grunsfeld and Feustel removed Wide-Field and Planetary Camera 2 and replaced it with Wide-Field Planetary Camera 2 and replaced it with Wide-Field Planetary Camera 2 and replaced it with Wide-Field Camera 3, which will allow Hubble to take extremely Camera 3, which will allow Hubble to take extremely Camera 3, which will allow Hubble to take extremely clear, detailed photos over a wider range of colors clear, detailed photos over a wider range of colors clear, detailed photos over a wider range of colors than WFPC2. Feustel struggled to loosen a bolt so than WFPC2. Feustel struggled to loosen a bolt so than WFPC2. Feustel struggled to loosen a bolt so he could remove WFPC2. Engineers on the ground he could remove WFPC2. Engineers on the ground he could remove WFPC2. Engineers on the ground theorized the low temperatures in space had altered theorized the low temperatures in space had altered theorized the low temperatures in space had altered the grease in the tool used to tighten the bolt dur- the grease in the tool used to tighten the bolt dur- the grease in the tool used to tighten the bolt dur- ing installation in 1993 and that more torque was ing installation in 1993 and that more torque was ing installation in 1993 and that more torque was needed to loosen the bolt than originally speci- needed to loosen the bolt than originally speci- needed to loosen the bolt than originally speci- fied. The danger lay in shearing off the bolt, which fied. The danger lay in shearing off the bolt, which fied. The danger lay in shearing off the bolt, which would have made it impossible to remove WFPC2. would have made it impossible to remove WFPC2. would have made it impossible to remove WFPC2. Grunsfeld and Feustel also replaced the telescope’s Grunsfeld and Feustel also replaced the telescope’s Grunsfeld and Feustel also replaced the telescope’s malfunctioning Science Instrument Command and malfunctioning Science Instrument Command and malfunctioning Science Instrument Command and Data Handling (SIC&DH) unit, which formats sci- Data Handling (SIC&DH) unit, which formats sci- Data Handling (SIC&DH) unit, which formats sci- ence data for transmission to Earth. EVA 2, 7 hours, ence data for transmission to Earth. EVA 2, 7 hours, ence data for transmission to Earth. EVA 2, 7 hours, 56 minutes; Good and Massimino replaced all three 56 minutes; Good and Massimino replaced all three 56 minutes; Good and Massimino replaced all three of Hubble’s rate sensing units, each of which con- of Hubble’s rate sensing units, each of which con- of Hubble’s rate sensing units, each of which con- tains two gyroscopes. In addition, they replaced the tains two gyroscopes. In addition, they replaced the tains two gyroscopes. In addition, they replaced the battery module in Hubble’s bay 2. EVA 3, 6 hours, battery module in Hubble’s bay 2. EVA 3, 6 hours, battery module in Hubble’s bay 2. EVA 3, 6 hours, 36 minutes; Grunsfeld and Feustel removed the 36 minutes; Grunsfeld and Feustel removed the 36 minutes; Grunsfeld and Feustel removed the refrigerator-size Corrective Optics Space Telescope refrigerator-size Corrective Optics Space Telescope refrigerator-size Corrective Optics Space Telescope Axial Replacement (COSTAR) installed in 1993 and Axial Replacement (COSTAR) installed in 1993 and Axial Replacement (COSTAR) installed in 1993 and then installed the new Cosmic Origins Spectro- then installed the new Cosmic Origins Spectro- then installed the new Cosmic Origins Spectro- graph (COS). They also repaired the Advanced graph (COS). They also repaired the Advanced graph (COS). They also repaired the Advanced Camera for Surveys (ACS), one of Hubble’s primary Camera for Surveys (ACS), one of Hubble’s primary Camera for Surveys (ACS), one of Hubble’s primary cameras, which had stopped working in 2007. The cameras, which had stopped working in 2007. The cameras, which had stopped working in 2007. The ACS was designed to operate in three modes: a ACS was designed to operate in three modes: a ACS was designed to operate in three modes: a high-resolution channel, a wide-field camera, and high-resolution channel, a wide-field camera, and high-resolution channel, a wide-field camera, and a so-called solar blind channel. Tests indicate the a so-called solar blind channel. Tests indicate the a so-called solar blind channel. Tests indicate the high-resolution channel was not restored. EVA 4, high-resolution channel was not restored. EVA 4, 8 high-resolution channel was not restored. EVA 4, 8 8 hours, 2 minutes; Good and Massimino repaired hours, 2 minutes; Good and Massimino repaired hours, 2 minutes; Good and Massimino repaired

Y-114 Y-114 Y-114 STS-125 Mission Facts (Cont) STS-125 Mission Facts (Cont) STS-125 Mission Facts (Cont)

the Space Telescope Imaging Spectrograph (STIS), the Space Telescope Imaging Spectrograph (STIS), the Space Telescope Imaging Spectrograph (STIS), which had ceased working in 2004, by replacing which had ceased working in 2004, by replacing which had ceased working in 2004, by replacing a power supply board. Massimino encountered a power supply board. Massimino encountered a power supply board. Massimino encountered a stripped bolt holding a handrail that needed to a stripped bolt holding a handrail that needed to a stripped bolt holding a handrail that needed to come off to reach the STIS, then had to unscrew come off to reach the STIS, then had to unscrew come off to reach the STIS, then had to unscrew more than 110 small fasteners to reach the STIS more than 110 small fasteners to reach the STIS more than 110 small fasteners to reach the STIS and not allow any of the fasteners to float away. and not allow any of the fasteners to float away. and not allow any of the fasteners to float away. EVA 5, 7 hours, 2 minutes; Grunsfeld and Feustel EVA 5, 7 hours, 2 minutes; Grunsfeld and Feustel EVA 5, 7 hours, 2 minutes; Grunsfeld and Feustel removed a battery module containing three batter- removed a battery module containing three batter- removed a battery module containing three batter- ies from bay 3 and replaced it with a fresh module. ies from bay 3 and replaced it with a fresh module. ies from bay 3 and replaced it with a fresh module. They also removed and replaced Fine Guidance They also removed and replaced Fine Guidance They also removed and replaced Fine Guidance Sensor (FGS) 2.In addition, Grunsfeld and Feustel Sensor (FGS) 2.In addition, Grunsfeld and Feustel Sensor (FGS) 2.In addition, Grunsfeld and Feustel installed New Outer Blanket Layers (NOBL) on three installed New Outer Blanket Layers (NOBL) on three installed New Outer Blanket Layers (NOBL) on three bays on the outside of the telescope. Hubble can bays on the outside of the telescope. Hubble can bays on the outside of the telescope. Hubble can go through temperature swings of a few hundred go through temperature swings of a few hundred go through temperature swings of a few hundred degrees every time it passes between daylight and degrees every time it passes between daylight and degrees every time it passes between daylight and darkness. darkness. darkness. Of Note: Michael Massimino became the first person to Of Note: Michael Massimino became the first person to Of Note: Michael Massimino became the first person to use Twitter in space. Known among the Twittering use Twitter in space. Known among the Twittering use Twitter in space. Known among the Twittering crowd as Astro–Mike, he had been updating his crowd as Astro–Mike, he had been updating his crowd as Astro–Mike, he had been updating his more than 300,000 followers for two months prior more than 300,000 followers for two months prior more than 300,000 followers for two months prior to the mission. Massimino sent several tweets from to the mission. Massimino sent several tweets from to the mission. Massimino sent several tweets from orbit, though none while on a spacewalk. orbit, though none while on a spacewalk. orbit, though none while on a spacewalk. For every shuttle mission since Columbia, there has For every shuttle mission since Columbia, there has For every shuttle mission since Columbia, there has been a contingency plan in place to allow another been a contingency plan in place to allow another been a contingency plan in place to allow another shuttle to be launched if needed to rescue a strand- shuttle to be launched if needed to rescue a strand- shuttle to be launched if needed to rescue a strand- ed shuttle crew. On ISS missions, a stranded crew ed shuttle crew. On ISS missions, a stranded crew ed shuttle crew. On ISS missions, a stranded crew can wait longer at the station than would have been can wait longer at the station than would have been can wait longer at the station than would have been the case for Atlantis. For STS-125, another shuttle the case for Atlantis. For STS-125, another shuttle the case for Atlantis. For STS-125, another shuttle was standing ready on Kennedy Space Center’s was standing ready on Kennedy Space Center’s was standing ready on Kennedy Space Center’s launch pad 39B. If needed, space shuttle Endeav- launch pad 39B. If needed, space shuttle Endeav- launch pad 39B. If needed, space shuttle Endeav- our, designated mission STS-400 and manned by our, designated mission STS-400 and manned by our, designated mission STS-400 and manned by the flight deck crew of mission STS-126, was ready the flight deck crew of mission STS-126, was ready the flight deck crew of mission STS-126, was ready to fly to Hubble and retrieve Atlantis’ crew within to fly to Hubble and retrieve Atlantis’ crew within to fly to Hubble and retrieve Atlantis’ crew within days. Endeavour stayed on rescue stand-by until days. Endeavour stayed on rescue stand-by until days. Endeavour stayed on rescue stand-by until May 21. May 21. May 21. With the conclusion of the STS-125 mission, 23 With the conclusion of the STS-125 mission, 23 With the conclusion of the STS-125 mission, 23 spacewalks have been dedicated to Hubble, total- spacewalks have been dedicated to Hubble, total- spacewalks have been dedicated to Hubble, total- ing 166 hours, 6 minutes. EVA 4 during STS-125 is ing 166 hours, 6 minutes. EVA 4 during STS-125 is ing 166 hours, 6 minutes. EVA 4 during STS-125 is the sixth longest spacewalk in U.S. history. EVA 2 is the sixth longest spacewalk in U.S. history. EVA 2 is the sixth longest spacewalk in U.S. history. EVA 2 is the ninth longest. the ninth longest. the ninth longest. It will take months to calibrate Hubble’s systems so It will take months to calibrate Hubble’s systems so It will take months to calibrate Hubble’s systems so it can resume scientific observations, with astrono- it can resume scientific observations, with astrono- it can resume scientific observations, with astrono- mers focusing on stars of well-established bright- mers focusing on stars of well-established bright- mers focusing on stars of well-established bright- ness. Great care will be taken to keep the telescope ness. Great care will be taken to keep the telescope ness. Great care will be taken to keep the telescope from facing the Earth’s blindingly bright reflection. from facing the Earth’s blindingly bright reflection. from facing the Earth’s blindingly bright reflection. The upgrades will extend its life to 2014, when a The upgrades will extend its life to 2014, when a The upgrades will extend its life to 2014, when a replacement, the James Webb Space Telescope, replacement, the James Webb Space Telescope, replacement, the James Webb Space Telescope, is scheduled for launch. It is estimated that around is scheduled for launch. It is estimated that around is scheduled for launch. It is estimated that around 2025, Hubble will begin to fall to Earth. A rocket will 2025, Hubble will begin to fall to Earth. A rocket will 2025, Hubble will begin to fall to Earth. A rocket will be launched with instruments that will robotically be launched with instruments that will robotically be launched with instruments that will robotically latch onto Hubble and guide it to a splashdown in latch onto Hubble and guide it to a splashdown in latch onto Hubble and guide it to a splashdown in the Pacific Ocean. the Pacific Ocean. the Pacific Ocean.

Y-115 Y-115 Y-115 STS-127 Mission Facts — Endeavour — STS-127 Mission Facts — Endeavour — STS-127 Mission Facts — Endeavour — July 15–31, 2009 July 15–31, 2009 July 15–31, 2009

Commander: Mark L. Polansky Commander: Mark L. Polansky Commander: Mark L. Polansky Pilot: Douglas G. Hurley Pilot: Douglas G. Hurley Pilot: Douglas G. Hurley Mission Specialist: Christopher J. Cassidy Mission Specialist: Christopher J. Cassidy Mission Specialist: Christopher J. Cassidy Mission Specialist: Thomas H. Marshburn Mission Specialist: Thomas H. Marshburn Mission Specialist: Thomas H. Marshburn Mission Specialist: Julie Payette, Canadian Space Mission Specialist: Julie Payette, Canadian Space Mission Specialist: Julie Payette, Canadian Space Agency Agency Agency Mission Specialist: David A. Wolf Mission Specialist: David A. Wolf Mission Specialist: David A. Wolf ISS Crew Member: Timothy L. Kopra—up only ISS Crew Member: Timothy L. Kopra—up only ISS Crew Member: Timothy L. Kopra—up only ISS Crew Member: Koichi Wakata—down only ISS Crew Member: Koichi Wakata—down only ISS Crew Member: Koichi Wakata—down only Launched: 6:03 p.m. EDT, launch pad 39A, Kennedy Launched: 6:03 p.m. EDT, launch pad 39A, Kennedy Launched: 6:03 p.m. EDT, launch pad 39A, Kennedy Space Center, Fla. Space Center, Fla. Space Center, Fla. Mission Duration: 360 hours (15 days), 16 hours, 45 Mission Duration: 360 hours (15 days), 16 hours, 45 Mission Duration: 360 hours (15 days), 16 hours, 45 minutes minutes minutes Miles Traveled: 6,547,853 statute miles Miles Traveled: 6,547,853 statute miles Miles Traveled: 6,547,853 statute miles Orbits of Earth: 248 Orbits of Earth: 248 Orbits of Earth: 248 Inclination: 51.6 degrees Inclination: 51.6 degrees Inclination: 51.6 degrees Orbital Altitude: 191 nautical miles Orbital Altitude: 191 nautical miles Orbital Altitude: 191 nautical miles Lift-Off Weight: 4,519,002 pounds Lift-Off Weight: 4,519,002 pounds Lift-Off Weight: 4,519,002 pounds Orbiter Weight at Lift-Off: 264,198 pounds Orbiter Weight at Lift-Off: 264,198 pounds Orbiter Weight at Lift-Off: 264,198 pounds Payload Weight Up: 24,638 pounds Payload Weight Up: 24,638 pounds Payload Weight Up: 24,638 pounds Orbiter Weight at Landing: 214,747 pounds Orbiter Weight at Landing: 214,747 pounds Orbiter Weight at Landing: 214,747 pounds Payload Weight Down: 10,479 pounds Payload Weight Down: 10,479 pounds Payload Weight Down: 10,479 pounds Landed: 10:48 a.m. EDT, concrete runway 15, Kennedy Landed: 10:48 a.m. EDT, concrete runway 15, Kennedy Landed: 10:48 a.m. EDT, concrete runway 15, Kennedy Space Center, Fla. Space Center, Fla. Space Center, Fla. Payload: ISS Assembly Flight 2J/A; Kibo Japanese Ex- Payload: ISS Assembly Flight 2J/A; Kibo Japanese Ex- Payload: ISS Assembly Flight 2J/A; Kibo Japanese Ex- periment Module Exposed Facility (JEM–EF), Kibo periment Module Exposed Facility (JEM–EF), Kibo periment Module Exposed Facility (JEM–EF), Kibo Japanese Experiment Logistics Module–Exposed Japanese Experiment Logistics Module–Exposed Japanese Experiment Logistics Module–Exposed Section (ELM–ES); Integrated Cargo Carrier (ICC); Section (ELM–ES); Integrated Cargo Carrier (ICC); Section (ELM–ES); Integrated Cargo Carrier (ICC); crew exchange crew exchange crew exchange Extravehicular Activity (EVA) conducted by David Wolf, Extravehicular Activity (EVA) conducted by David Wolf, Extravehicular Activity (EVA) conducted by David Wolf, Timothy Kopra, Thomas Marshburn, and Chris- Timothy Kopra, Thomas Marshburn, and Chris- Timothy Kopra, Thomas Marshburn, and Chris- topher Cassidy during five spacewalks for a total topher Cassidy during five spacewalks for a total topher Cassidy during five spacewalks for a total of 30 hours, 30 minutes. The spacewalkers were of 30 hours, 30 minutes. The spacewalkers were of 30 hours, 30 minutes. The spacewalkers were assisted by Mark Polansky and Julie Payette using assisted by Mark Polansky and Julie Payette using assisted by Mark Polansky and Julie Payette using the shuttle’s Canadarm and Koichi Wakata and the shuttle’s Canadarm and Koichi Wakata and the shuttle’s Canadarm and Koichi Wakata and Douglas Hurley using the ISS Canadarm2. EVA 1, Douglas Hurley using the ISS Canadarm2. EVA 1, Douglas Hurley using the ISS Canadarm2. EVA 1, 5 hours, 32 minutes; Wolf and Kopra prepared the 5 hours, 32 minutes; Wolf and Kopra prepared the 5 hours, 32 minutes; Wolf and Kopra prepared the berthing mechanisms on the Kibo lab and the JEF berthing mechanisms on the Kibo lab and the JEF berthing mechanisms on the Kibo lab and the JEF for the installation. They also completed deploying for the installation. They also completed deploying for the installation. They also completed deploying an unpressurized cargo carrier attachment system an unpressurized cargo carrier attachment system an unpressurized cargo carrier attachment system on the P3 truss that had failed to unfurl during on the P3 truss that had failed to unfurl during on the P3 truss that had failed to unfurl during STS-119. EVA 2, 6 hours, 53 minutes; Wolf and STS-119. EVA 2, 6 hours, 53 minutes; Wolf and STS-119. EVA 2, 6 hours, 53 minutes; Wolf and Marshburn removed three hardware spares from Marshburn removed three hardware spares from Marshburn removed three hardware spares from an Integrated Cargo Carrier and attached them to a an Integrated Cargo Carrier and attached them to a an Integrated Cargo Carrier and attached them to a stowage platform on the P3 truss for long-term stor- stowage platform on the P3 truss for long-term stor- stowage platform on the P3 truss for long-term stor- age. EVA 3, 5 hours, 59 minutes; Wolf and Cassidy age. EVA 3, 5 hours, 59 minutes; Wolf and Cassidy age. EVA 3, 5 hours, 59 minutes; Wolf and Cassidy replaced two of six old solar array batteries on the replaced two of six old solar array batteries on the replaced two of six old solar array batteries on the P6 truss. These batteries are the oldest ones on the P6 truss. These batteries are the oldest ones on the P6 truss. These batteries are the oldest ones on the space station and are located at the end of the port space station and are located at the end of the port space station and are located at the end of the port side truss, hundreds of feet from the station’s core. side truss, hundreds of feet from the station’s core. side truss, hundreds of feet from the station’s core. Each battery weighs 367 pounds and is the size of Each battery weighs 367 pounds and is the size of Each battery weighs 367 pounds and is the size of a refrigerator. It was originally planned to replace a refrigerator. It was originally planned to replace a refrigerator. It was originally planned to replace

Y-116 Y-116 Y-116 STS-127 Mission Facts (Cont) STS-127 Mission Facts (Cont) STS-127 Mission Facts (Cont)

four batteries on EVA 3, but the spacewalk was four batteries on EVA 3, but the spacewalk was four batteries on EVA 3, but the spacewalk was ended early when it appeared there was a potential ended early when it appeared there was a potential ended early when it appeared there was a potential problem with the carbon dioxide scrubbing device problem with the carbon dioxide scrubbing device problem with the carbon dioxide scrubbing device on Cassidy’s spacesuit. EVA 4, 7 hours, 12 minutes; on Cassidy’s spacesuit. EVA 4, 7 hours, 12 minutes; on Cassidy’s spacesuit. EVA 4, 7 hours, 12 minutes; Cassidy and Marshburn replaced the remain- Cassidy and Marshburn replaced the remain- Cassidy and Marshburn replaced the remain- ing four solar array batteries on the P6 truss. EVA ing four solar array batteries on the P6 truss. EVA ing four solar array batteries on the P6 truss. EVA 5, 4 hours, 54 minutes; Cassidy and Marshburn 5, 4 hours, 54 minutes; Cassidy and Marshburn 5, 4 hours, 54 minutes; Cassidy and Marshburn installed video cameras on the front and back of the installed video cameras on the front and back of the installed video cameras on the front and back of the new JEM–EF, secured multilayer insulation around new JEM–EF, secured multilayer insulation around new JEM–EF, secured multilayer insulation around Dextre, split out power channels for two control mo- Dextre, split out power channels for two control mo- Dextre, split out power channels for two control mo- ment gyroscopes, tied down cables, and installed ment gyroscopes, tied down cables, and installed ment gyroscopes, tied down cables, and installed handrails and a portable foot restraint. handrails and a portable foot restraint. handrails and a portable foot restraint. Of Note: For the first time, 13 astronauts occupied the Of Note: For the first time, 13 astronauts occupied the Of Note: For the first time, 13 astronauts occupied the ISS at one time, the largest crew ever assembled ISS at one time, the largest crew ever assembled ISS at one time, the largest crew ever assembled on one space vehicle. All of the station’s interna- on one space vehicle. All of the station’s interna- on one space vehicle. All of the station’s interna- tional partners—NASA, the Russian space agency tional partners—NASA, the Russian space agency tional partners—NASA, the Russian space agency Roscosmos, the European Space Agency (ESA), Roscosmos, the European Space Agency (ESA), Roscosmos, the European Space Agency (ESA), the Japan Aerospace Exploration Agency (JAXA), the Japan Aerospace Exploration Agency (JAXA), the Japan Aerospace Exploration Agency (JAXA), and the Canadian Space Agency (CSA)—were and the Canadian Space Agency (CSA)—were and the Canadian Space Agency (CSA)—were represented on board the ISS. represented on board the ISS. represented on board the ISS. Mission specialist Christopher Cassidy became the Mission specialist Christopher Cassidy became the Mission specialist Christopher Cassidy became the 500th person in space. 500th person in space. 500th person in space. Julie Payette and Robert Thirsk became the first two Julie Payette and Robert Thirsk became the first two Julie Payette and Robert Thirsk became the first two Canadians in space at the same time. Canadians in space at the same time. Canadians in space at the same time. The crew of the ISS and space shuttle Endeavour The crew of the ISS and space shuttle Endeavour The crew of the ISS and space shuttle Endeavour honored the legacy of Apollo 11 by conducting honored the legacy of Apollo 11 by conducting honored the legacy of Apollo 11 by conducting a spacewalk on the same day that 40 years prior a spacewalk on the same day that 40 years prior a spacewalk on the same day that 40 years prior Neil Armstrong and Buzz Aldrin had walked on the Neil Armstrong and Buzz Aldrin had walked on the Neil Armstrong and Buzz Aldrin had walked on the moon for the first time. moon for the first time. moon for the first time. Two pairs of small research satellites—the Dual Two pairs of small research satellites—the Dual Two pairs of small research satellites—the Dual RF Astrodynamic GPS Orbital Navigation Satellite RF Astrodynamic GPS Orbital Navigation Satellite RF Astrodynamic GPS Orbital Navigation Satellite (DRAGONSat) and the Atmospheric Neutral Density (DRAGONSat) and the Atmospheric Neutral Density (DRAGONSat) and the Atmospheric Neutral Density Experiment–2 (ANDE-2)—were deployed from the Experiment–2 (ANDE-2)—were deployed from the Experiment–2 (ANDE-2)—were deployed from the space shuttle after it undocked from the ISS. space shuttle after it undocked from the ISS. space shuttle after it undocked from the ISS.

STS-128 Mission Facts — Discovery — STS-128 Mission Facts — Discovery — STS-128 Mission Facts — Discovery — Aug. 28–Sept. 11, 2009 Aug. 28–Sept. 11, 2009 Aug. 28–Sept. 11, 2009

Commander: Frederick W. Sturckow Commander: Frederick W. Sturckow Commander: Frederick W. Sturckow Pilot: Kevin A. Ford Pilot: Kevin A. Ford Pilot: Kevin A. Ford Mission Specialist: Patrick G. Forrester Mission Specialist: Patrick G. Forrester Mission Specialist: Patrick G. Forrester Mission Specialist: José M. Hernández Mission Specialist: José M. Hernández Mission Specialist: José M. Hernández Mission Specialist: Christer Fuglesang, European Space Mission Specialist: Christer Fuglesang, European Space Mission Specialist: Christer Fuglesang, European Space Agency (ESA) Agency (ESA) Agency (ESA) Mission Specialist: John D. Olivas Mission Specialist: John D. Olivas Mission Specialist: John D. Olivas ISS Crew Member: Nicole P. Stott—up only ISS Crew Member: Nicole P. Stott—up only ISS Crew Member: Nicole P. Stott—up only ISS Crew Member: Timothy L. Kopra—down only ISS Crew Member: Timothy L. Kopra—down only ISS Crew Member: Timothy L. Kopra—down only Launched: 11:59 p.m. EDT, launch pad 39A, Kennedy Launched: 11:59 p.m. EDT, launch pad 39A, Kennedy Launched: 11:59 p.m. EDT, launch pad 39A, Kennedy Space Center, Fla. Space Center, Fla. Space Center, Fla. Mission Duration: 312 hours (13 days), 20 hours, Mission Duration: 312 hours (13 days), 20 hours, Mission Duration: 312 hours (13 days), 20 hours, 54 minutes 54 minutes 54 minutes Miles Traveled: 5,755,275 statute miles Miles Traveled: 5,755,275 statute miles Miles Traveled: 5,755,275 statute miles

Y-117 Y-117 Y-117 STS-128 Mission Facts (Cont) STS-128 Mission Facts (Cont) STS-128 Mission Facts (Cont)

Orbits of Earth: 219 Orbits of Earth: 219 Orbits of Earth: 219 Inclination: 51.6 degrees Inclination: 51.6 degrees Inclination: 51.6 degrees Orbital Altitude: 188 nautical miles Orbital Altitude: 188 nautical miles Orbital Altitude: 188 nautical miles Lift-Off Weight: 4,522,852 pounds Lift-Off Weight: 4,522,852 pounds Lift-Off Weight: 4,522,852 pounds Orbiter Weight at Lift-Off: 267,689 pounds Orbiter Weight at Lift-Off: 267,689 pounds Orbiter Weight at Lift-Off: 267,689 pounds Payload Weight Up: 33,056 pounds Payload Weight Up: 33,056 pounds Payload Weight Up: 33,056 pounds Orbiter Weight at Landing: 225,860 pounds Orbiter Weight at Landing: 225,860 pounds Orbiter Weight at Landing: 225,860 pounds Payload Weight Down: 21,614 pounds Payload Weight Down: 21,614 pounds Payload Weight Down: 21,614 pounds Landed: 8:53 p.m. EDT, concrete runway 22, Edwards Air Landed: 8:53 p.m. EDT, concrete runway 22, Edwards Air Landed: 8:53 p.m. EDT, concrete runway 22, Edwards Air Force Base, Calif. Force Base, Calif. Force Base, Calif. Payload: ISS Assembly Flight 17A; Leonardo Multipur- Payload: ISS Assembly Flight 17A; Leonardo Multipur- Payload: ISS Assembly Flight 17A; Leonardo Multipur- pose Logistics Module carrying more than 16,000 pose Logistics Module carrying more than 16,000 pose Logistics Module carrying more than 16,000 pounds of supplies and equipment, including the pounds of supplies and equipment, including the pounds of supplies and equipment, including the Combined Operational Load Bearing External Combined Operational Load Bearing External Combined Operational Load Bearing External Resistance Treadmill (COLBERT); Fluids Integrated Resistance Treadmill (COLBERT); Fluids Integrated Resistance Treadmill (COLBERT); Fluids Integrated Rack, Materials Science Research Rack–1 and Mi- Rack, Materials Science Research Rack–1 and Mi- Rack, Materials Science Research Rack–1 and Mi- nus Eighty-Degree Laboratory Freezer for ISS; and nus Eighty-Degree Laboratory Freezer for ISS; and nus Eighty-Degree Laboratory Freezer for ISS; and new crew quarters for Robert Thirsk; Lightweight new crew quarters for Robert Thirsk; Lightweight new crew quarters for Robert Thirsk; Lightweight Multipurpose Carrier (LMC) with Ammonia Tank As- Multipurpose Carrier (LMC) with Ammonia Tank As- Multipurpose Carrier (LMC) with Ammonia Tank As- sembly (ATA); crew exchange sembly (ATA); crew exchange sembly (ATA); crew exchange Extravehicular Activity (EVA) conducted by Danny Extravehicular Activity (EVA) conducted by Danny Extravehicular Activity (EVA) conducted by Danny Olivas, Nicole Stott, and Christer Fuglesang dur- Olivas, Nicole Stott, and Christer Fuglesang dur- Olivas, Nicole Stott, and Christer Fuglesang dur- ing three spacewalks for a total of 20 hours, 15 ing three spacewalks for a total of 20 hours, 15 ing three spacewalks for a total of 20 hours, 15 minutes. EVA 1, 6 hours, 35 minutes; Olivas and minutes. EVA 1, 6 hours, 35 minutes; Olivas and minutes. EVA 1, 6 hours, 35 minutes; Olivas and Stott removed an ammonia tank assembly from the Stott removed an ammonia tank assembly from the Stott removed an ammonia tank assembly from the ISS port truss and two experiments—the European ISS port truss and two experiments—the European ISS port truss and two experiments—the European Technology Exposure Facility (EuTEF) and the Technology Exposure Facility (EuTEF) and the Technology Exposure Facility (EuTEF) and the Materials International Space Station Experiment Materials International Space Station Experiment Materials International Space Station Experiment (MISSE)—for return to Earth. EVA 2, 6 hours, 39 (MISSE)—for return to Earth. EVA 2, 6 hours, 39 (MISSE)—for return to Earth. EVA 2, 6 hours, 39 minutes; Olivas and Fuglesang installed a new minutes; Olivas and Fuglesang installed a new minutes; Olivas and Fuglesang installed a new ammonia tank assembly, which pushes ammonia ammonia tank assembly, which pushes ammonia ammonia tank assembly, which pushes ammonia through loops on the ISS truss to expel excess heat through loops on the ISS truss to expel excess heat through loops on the ISS truss to expel excess heat generated by the station’s residents and systems, generated by the station’s residents and systems, generated by the station’s residents and systems, and installed a portable foot restraint for use during and installed a portable foot restraint for use during and installed a portable foot restraint for use during upcoming missions. EVA 3, 7 hours, 01 minute; upcoming missions. EVA 3, 7 hours, 01 minute; upcoming missions. EVA 3, 7 hours, 01 minute; Olivas and Fuglesang set up a payload attach- Olivas and Fuglesang set up a payload attach- Olivas and Fuglesang set up a payload attach- ment system on the ISS starboard truss to be used ment system on the ISS starboard truss to be used ment system on the ISS starboard truss to be used on STS-130; replaced a rate gyro assembly and on STS-130; replaced a rate gyro assembly and on STS-130; replaced a rate gyro assembly and remote power control module; installed two GPS remote power control module; installed two GPS remote power control module; installed two GPS antennas; and removed a slide wire on the Unity antennas; and removed a slide wire on the Unity antennas; and removed a slide wire on the Unity module. module. module. Of Note: Astronaut José Hernández grew up in a migrant Of Note: Astronaut José Hernández grew up in a migrant Of Note: Astronaut José Hernández grew up in a migrant farming family and didn’t learn English until he was farming family and didn’t learn English until he was farming family and didn’t learn English until he was 12. During his senior year of high school, listening 12. During his senior year of high school, listening 12. During his senior year of high school, listening to the radio while hoeing sugar beets, he learned to the radio while hoeing sugar beets, he learned to the radio while hoeing sugar beets, he learned that NASA had recruited its first Hispanic astronaut, that NASA had recruited its first Hispanic astronaut, that NASA had recruited its first Hispanic astronaut, Franklin Chang-Diaz. Inspired, Hernández decided Franklin Chang-Diaz. Inspired, Hernández decided Franklin Chang-Diaz. Inspired, Hernández decided to pursue his interests in math and science, eventu- to pursue his interests in math and science, eventu- to pursue his interests in math and science, eventu- ally earning bachelor and master’s degrees in ally earning bachelor and master’s degrees in ally earning bachelor and master’s degrees in electrical engineering. He formed the “Reaching for electrical engineering. He formed the “Reaching for electrical engineering. He formed the “Reaching for the Stars” foundation in his hometown of Stockton, the Stars” foundation in his hometown of Stockton, the Stars” foundation in his hometown of Stockton, Calif., to inspire local youth to excel in math, sci- Calif., to inspire local youth to excel in math, sci- Calif., to inspire local youth to excel in math, sci- ence, engineering, and technology. Hernández is ence, engineering, and technology. Hernández is ence, engineering, and technology. Hernández is NASA’s first bilingual Twittering astronaut, sending NASA’s first bilingual Twittering astronaut, sending NASA’s first bilingual Twittering astronaut, sending Spanish and English tweets from Astro_Jose. Spanish and English tweets from Astro_Jose. Spanish and English tweets from Astro_Jose.

Y-118 Y-118 Y-118 STS-129 Mission Facts — Atlantis — STS-129 Mission Facts — Atlantis — STS-129 Mission Facts — Atlantis — Nov. 16–27, 2009 Nov. 16–27, 2009 Nov. 16–27, 2009

Commander: Charles O. Hobaugh Commander: Charles O. Hobaugh Commander: Charles O. Hobaugh Pilot: Barry E. Wilmore Pilot: Barry E. Wilmore Pilot: Barry E. Wilmore Mission Specialist: Randolph J. Bresnik Mission Specialist: Randolph J. Bresnik Mission Specialist: Randolph J. Bresnik Mission Specialist: Michael J. Foreman Mission Specialist: Michael J. Foreman Mission Specialist: Michael J. Foreman Mission Specialist: Leland D. Melvin Mission Specialist: Leland D. Melvin Mission Specialist: Leland D. Melvin Mission Specialist: Robert L. Satcher Jr. Mission Specialist: Robert L. Satcher Jr. Mission Specialist: Robert L. Satcher Jr. ISS Crew Member: Nicole P. Stott—down only ISS Crew Member: Nicole P. Stott—down only ISS Crew Member: Nicole P. Stott—down only Launched: 2:28 p.m. EST, launch pad 39A, Launched: 2:28 p.m. EST, launch pad 39A, Launched: 2:28 p.m. EST, launch pad 39A, Kennedy Space Center, Fla. Kennedy Space Center, Fla. Kennedy Space Center, Fla. Mission Duration: 240 hours (10 days), Mission Duration: 240 hours (10 days), Mission Duration: 240 hours (10 days), 19 hours, 16 minutes 19 hours, 16 minutes 19 hours, 16 minutes Miles Traveled: 4,490,138 statute miles Miles Traveled: 4,490,138 statute miles Miles Traveled: 4,490,138 statute miles Orbits of Earth: 171 Orbits of Earth: 171 Orbits of Earth: 171 Inclination: 51.6 degrees Inclination: 51.6 degrees Inclination: 51.6 degrees Orbital Altitude: 191 nautical miles (rendezvous) Orbital Altitude: 191 nautical miles (rendezvous) Orbital Altitude: 191 nautical miles (rendezvous) Lift-Off Weight: 4,522,269 pounds Lift-Off Weight: 4,522,269 pounds Lift-Off Weight: 4,522,269 pounds Orbiter Weight at Lift-Off: 266,310 pounds Orbiter Weight at Lift-Off: 266,310 pounds Orbiter Weight at Lift-Off: 266,310 pounds Payload Weight Up: 29,372 pounds Payload Weight Up: 29,372 pounds Payload Weight Up: 29,372 pounds Orbiter Weight at Landing: 205,420 pounds Orbiter Weight at Landing: 205,420 pounds Orbiter Weight at Landing: 205,420 pounds Payload Weight Down: 2,933 pounds Payload Weight Down: 2,933 pounds Payload Weight Down: 2,933 pounds Landed: 9:45 a.m. EST, concrete runway 33, Landed: 9:45 a.m. EST, concrete runway 33, Landed: 9:45 a.m. EST, concrete runway 33, Kennedy Space Center, Fla. Kennedy Space Center, Fla. Kennedy Space Center, Fla. Payload: ISS Assembly Flight ULF3; deliver and integrate Payload: ISS Assembly Flight ULF3; deliver and integrate Payload: ISS Assembly Flight ULF3; deliver and integrate ExPRESS Logistics Carrier 1 and 2 (ELC1 and ExPRESS Logistics Carrier 1 and 2 (ELC1 and ExPRESS Logistics Carrier 1 and 2 (ELC1 and ELC2) carrying numerous orbital replacement units ELC2) carrying numerous orbital replacement units ELC2) carrying numerous orbital replacement units too big and massive to fly in any of the vehicles too big and massive to fly in any of the vehicles too big and massive to fly in any of the vehicles that will be left when the space shuttle retires, such that will be left when the space shuttle retires, such that will be left when the space shuttle retires, such as control moment gyroscopes, a battery charge as control moment gyroscopes, a battery charge as control moment gyroscopes, a battery charge discharge unit, a plasma contactor unit, nitrogen discharge unit, a plasma contactor unit, nitrogen discharge unit, a plasma contactor unit, nitrogen tanks, cooling system pump module assemblies, tanks, cooling system pump module assemblies, tanks, cooling system pump module assemblies, high-pressure gas tanks, ammonia tanks, a latching high-pressure gas tanks, ammonia tanks, a latching high-pressure gas tanks, ammonia tanks, a latching end effector for the station’s robotics, and a trailing end effector for the station’s robotics, and a trailing end effector for the station’s robotics, and a trailing umbilical system reel assembly; Materials Interna- umbilical system reel assembly; Materials Interna- umbilical system reel assembly; Materials Interna- tional Space Station Experiment (MISSE) 7; return tional Space Station Experiment (MISSE) 7; return tional Space Station Experiment (MISSE) 7; return ISS crew member Nicole Stott to Earth ISS crew member Nicole Stott to Earth ISS crew member Nicole Stott to Earth Extravehicular Activity (EVA) conducted by Extravehicular Activity (EVA) conducted by Extravehicular Activity (EVA) conducted by Mike Foreman, Robert Satcher, and Randy Bresnik Mike Foreman, Robert Satcher, and Randy Bresnik Mike Foreman, Robert Satcher, and Randy Bresnik during three spacewalks for a total of 18 hours, during three spacewalks for a total of 18 hours, during three spacewalks for a total of 18 hours, 27 minutes. Leland Melvin and Randy Bresnik 27 minutes. Leland Melvin and Randy Bresnik 27 minutes. Leland Melvin and Randy Bresnik removed ELC1 from Atlantis’ payload bay using removed ELC1 from Atlantis’ payload bay using removed ELC1 from Atlantis’ payload bay using the shuttle’s robotic arm and handed it off to the the shuttle’s robotic arm and handed it off to the the shuttle’s robotic arm and handed it off to the station’s robotic arm controlled by Barry Wilmore station’s robotic arm controlled by Barry Wilmore station’s robotic arm controlled by Barry Wilmore and ISS crew member Jeff Williams, who installed and ISS crew member Jeff Williams, who installed and ISS crew member Jeff Williams, who installed the carrier on the ISS P3 truss. ELC2 was installed the carrier on the ISS P3 truss. ELC2 was installed the carrier on the ISS P3 truss. ELC2 was installed on the ISS S3 truss using the station’s robotic on the ISS S3 truss using the station’s robotic on the ISS S3 truss using the station’s robotic arm operated by Melvin and Nicole Stott. EVA 1, 6 arm operated by Melvin and Nicole Stott. EVA 1, 6 arm operated by Melvin and Nicole Stott. EVA 1, 6 hours, 37 minutes; Foreman and Satcher installed hours, 37 minutes; Foreman and Satcher installed hours, 37 minutes; Foreman and Satcher installed a spare S-band antenna assembly on the ISS Z1 a spare S-band antenna assembly on the ISS Z1 a spare S-band antenna assembly on the ISS Z1 truss, installed antenna cables on Destiny, replaced truss, installed antenna cables on Destiny, replaced truss, installed antenna cables on Destiny, replaced a handrail on Unity, and installed a Payload Attach a handrail on Unity, and installed a Payload Attach a handrail on Unity, and installed a Payload Attach System (PAS) on the Earth-facing side of the S3 System (PAS) on the Earth-facing side of the S3 System (PAS) on the Earth-facing side of the S3 truss. EVA 2, 6 hours, 8 minutes; Foreman and truss. EVA 2, 6 hours, 8 minutes; Foreman and truss. EVA 2, 6 hours, 8 minutes; Foreman and

Y-119 Y-119 Y-119 STS-129 Mission Facts (Cont) STS-129 Mission Facts (Cont) STS-129 Mission Facts (Cont)

Bresnik installed the Grappling Adaptor to On-orbit Bresnik installed the Grappling Adaptor to On-orbit Bresnik installed the Grappling Adaptor to On-orbit Railing Assembly (GATOR) on a Columbus handrail, Railing Assembly (GATOR) on a Columbus handrail, Railing Assembly (GATOR) on a Columbus handrail, relocated the station’s floating potential measure- relocated the station’s floating potential measure- relocated the station’s floating potential measure- ment unit to the P1 truss, installed a second PAS ment unit to the P1 truss, installed a second PAS ment unit to the P1 truss, installed a second PAS on the upper part of the S3 truss, deployed a third on the upper part of the S3 truss, deployed a third on the upper part of the S3 truss, deployed a third PAS on the S3 truss, and installed a wireless video PAS on the S3 truss, and installed a wireless video PAS on the S3 truss, and installed a wireless video system on S3. EVA 3, 5 hours, 42 minutes; Satcher system on S3. EVA 3, 5 hours, 42 minutes; Satcher system on S3. EVA 3, 5 hours, 42 minutes; Satcher and Bresnik installed a high-pressure oxygen tank and Bresnik installed a high-pressure oxygen tank and Bresnik installed a high-pressure oxygen tank that had been stored on ELC2 and subsequently that had been stored on ELC2 and subsequently that had been stored on ELC2 and subsequently placed by the Quest airlock by Melvin and Wilmore placed by the Quest airlock by Melvin and Wilmore placed by the Quest airlock by Melvin and Wilmore using the ISS robotic arm. Satcher and Bresnik also using the ISS robotic arm. Satcher and Bresnik also using the ISS robotic arm. Satcher and Bresnik also installed MISSE 7 on ELC2. installed MISSE 7 on ELC2. installed MISSE 7 on ELC2. Of Note: While Randy Bresnik was busy with EVA 2, his Of Note: While Randy Bresnik was busy with EVA 2, his Of Note: While Randy Bresnik was busy with EVA 2, his wife, Rebecca, was busy on Earth giving birth to wife, Rebecca, was busy on Earth giving birth to wife, Rebecca, was busy on Earth giving birth to their daughter, Abigail Mae Bresnik, born Nov. 21, their daughter, Abigail Mae Bresnik, born Nov. 21, their daughter, Abigail Mae Bresnik, born Nov. 21, 2009, with an Earth weight of 6 pounds, 13 ounces. 2009, with an Earth weight of 6 pounds, 13 ounces. 2009, with an Earth weight of 6 pounds, 13 ounces. Abigail was born after her father completed his first Abigail was born after her father completed his first Abigail was born after her father completed his first spacewalk, during which time he was not in contact spacewalk, during which time he was not in contact spacewalk, during which time he was not in contact with the hospital. Bresnik is not the first astronaut to with the hospital. Bresnik is not the first astronaut to with the hospital. Bresnik is not the first astronaut to coach his wife through labor from orbit. Mike Fincke coach his wife through labor from orbit. Mike Fincke coach his wife through labor from orbit. Mike Fincke was on the ISS in 2004 when his wife gave birth to was on the ISS in 2004 when his wife gave birth to was on the ISS in 2004 when his wife gave birth to their daughter. their daughter. their daughter.

For the first time, NASA invited its Twitter followers to For the first time, NASA invited its Twitter followers to For the first time, NASA invited its Twitter followers to sign up online for the chance to see a space shuttle sign up online for the chance to see a space shuttle sign up online for the chance to see a space shuttle launch in person. The 100 “tweeps,” who financed launch in person. The 100 “tweeps,” who financed launch in person. The 100 “tweeps,” who financed their own travel, represented 21 states plus the their own travel, represented 21 states plus the their own travel, represented 21 states plus the District of Columbia, as well as five countries, District of Columbia, as well as five countries, District of Columbia, as well as five countries, including Morocco and New Zealand. Astronauts including Morocco and New Zealand. Astronauts including Morocco and New Zealand. Astronauts have been tweeting from Earth and orbit since have been tweeting from Earth and orbit since have been tweeting from Earth and orbit since spring 2009, but this tweetup was the first from spring 2009, but this tweetup was the first from spring 2009, but this tweetup was the first from Kennedy Space Center. Kennedy Space Center. Kennedy Space Center.

Y-120 Y-120 Y-120 UPCOMING SPACE SHUTTLE MISSIONS UPCOMING SPACE SHUTTLE MISSIONS UPCOMING SPACE SHUTTLE MISSIONS STS-130 Flight Crew STS-130 Flight Crew STS-130 Flight Crew

Commander: George D. Zamka (second flight) Commander: George D. Zamka (second flight) Commander: George D. Zamka (second flight) Pilot: Terry W. Virts Jr. (first flight) Pilot: Terry W. Virts Jr. (first flight) Pilot: Terry W. Virts Jr. (first flight) Mission Specialist: Robert L. Behnken (second flight) Mission Specialist: Robert L. Behnken (second flight) Mission Specialist: Robert L. Behnken (second flight) Mission Specialist: Kathryn P. Hire (second flight) Mission Specialist: Kathryn P. Hire (second flight) Mission Specialist: Kathryn P. Hire (second flight) Mission Specialist: Nicholas J.M. Patrick (second flight) Mission Specialist: Nicholas J.M. Patrick (second flight) Mission Specialist: Nicholas J.M. Patrick (second flight) Mission Specialist: Stephen K. Robinson (fourth flight) Mission Specialist: Stephen K. Robinson (fourth flight) Mission Specialist: Stephen K. Robinson (fourth flight) Payload: ISS Assembly Flight 20A; Node 3 “Tranquil- Payload: ISS Assembly Flight 20A; Node 3 “Tranquil- Payload: ISS Assembly Flight 20A; Node 3 “Tranquil- ity,” the final U.S. pressurized module, named in ity,” the final U.S. pressurized module, named in ity,” the final U.S. pressurized module, named in honor of the 40th anniversary of Apollo 11 landing honor of the 40th anniversary of Apollo 11 landing honor of the 40th anniversary of Apollo 11 landing on the moon’s Sea of Tranquility; and the Cupola, on the moon’s Sea of Tranquility; and the Cupola, on the moon’s Sea of Tranquility; and the Cupola, a robotics work station with six windows around its a robotics work station with six windows around its a robotics work station with six windows around its sides and another in the center that provides a 360- sides and another in the center that provides a 360- sides and another in the center that provides a 360- degree view around the ISS degree view around the ISS degree view around the ISS Projected launch date is February 2010, with Endeavour Projected launch date is February 2010, with Endeavour Projected launch date is February 2010, with Endeavour (OV-105) in its 24th fl ight (OV-105) in its 24th fl ight (OV-105) in its 24th fl ight

STS-131 Flight Crew STS-131 Flight Crew STS-131 Flight Crew

Commander: Alan G. Poindexter (second flight) Commander: Alan G. Poindexter (second flight) Commander: Alan G. Poindexter (second flight) Pilot: James P. Dutton Jr. (first flight) Pilot: James P. Dutton Jr. (first flight) Pilot: James P. Dutton Jr. (first flight) Mission Specialist: Richard A. Mastracchio (third flight) Mission Specialist: Richard A. Mastracchio (third flight) Mission Specialist: Richard A. Mastracchio (third flight) Mission Specialist: Dorothy M. Metcalf-Lindenburger Mission Specialist: Dorothy M. Metcalf-Lindenburger Mission Specialist: Dorothy M. Metcalf-Lindenburger (first flight) (first flight) (first flight) Mission Specialist: Clayton C. Anderson (third flight) Mission Specialist: Clayton C. Anderson (third flight) Mission Specialist: Clayton C. Anderson (third flight) Mission Specialist: Stephanie D. Wilson (third flight) Mission Specialist: Stephanie D. Wilson (third flight) Mission Specialist: Stephanie D. Wilson (third flight) Mission Specialist: Naoko Yamazaki, Japan Aerospace Mission Specialist: Naoko Yamazaki, Japan Aerospace Mission Specialist: Naoko Yamazaki, Japan Aerospace Exploration Agency (JAXA) (first flight) Exploration Agency (JAXA) (first flight) Exploration Agency (JAXA) (first flight) Payload: ISS Assembly Flight 19A; Raffaello Multipurpose Payload: ISS Assembly Flight 19A; Raffaello Multipurpose Payload: ISS Assembly Flight 19A; Raffaello Multipurpose Logistics Module; Lightweight Multi-Purpose Experi- Logistics Module; Lightweight Multi-Purpose Experi- Logistics Module; Lightweight Multi-Purpose Experi- ment Support Structure Carrier (LMC) ment Support Structure Carrier (LMC) ment Support Structure Carrier (LMC) Projected launch date is March 2010, with Discovery Projected launch date is March 2010, with Discovery Projected launch date is March 2010, with Discovery (OV-103) in its 38th fl ight (OV-103) in its 38th fl ight (OV-103) in its 38th fl ight

STS-132 Flight Crew STS-132 Flight Crew STS-132 Flight Crew

Commander: Kenneth T. Ham (second flight) Commander: Kenneth T. Ham (second flight) Commander: Kenneth T. Ham (second flight) Pilot: Dominic A. Antonelli (second flight) Pilot: Dominic A. Antonelli (second flight) Pilot: Dominic A. Antonelli (second flight) Mission Specialist: Stephen G. Bowen (second flight) Mission Specialist: Stephen G. Bowen (second flight) Mission Specialist: Stephen G. Bowen (second flight) Mission Specialist: Michael T. Good (second flight) Mission Specialist: Michael T. Good (second flight) Mission Specialist: Michael T. Good (second flight) Mission Specialist: Piers J. Sellers (third flight) Mission Specialist: Piers J. Sellers (third flight) Mission Specialist: Piers J. Sellers (third flight) Mission Specialist: Garrett E. Reisman (third flight) Mission Specialist: Garrett E. Reisman (third flight) Mission Specialist: Garrett E. Reisman (third flight) Payload: ISS Assembly Flight ULF4; Integrated Cargo Payload: ISS Assembly Flight ULF4; Integrated Cargo Payload: ISS Assembly Flight ULF4; Integrated Cargo Carrier (ICC); Mini-Research Module 1 (MRM1); Carrier (ICC); Mini-Research Module 1 (MRM1); Carrier (ICC); Mini-Research Module 1 (MRM1); last delivery of an ISS module last delivery of an ISS module last delivery of an ISS module Projected launch date is May 2010, with Atlantis Projected launch date is May 2010, with Atlantis Projected launch date is May 2010, with Atlantis (OV-104) in its 32nd and fi nal fl ight (OV-104) in its 32nd and fi nal fl ight (OV-104) in its 32nd and fi nal fl ight

G-1 G-1 G-1 STS-134 Flight Crew STS-134 Flight Crew STS-134 Flight Crew

Commander: Mark E. Kelly (fourth flight) Commander: Mark E. Kelly (fourth flight) Commander: Mark E. Kelly (fourth flight) Pilot: Gregory H. Johnson (second flight) Pilot: Gregory H. Johnson (second flight) Pilot: Gregory H. Johnson (second flight) Mission Specialist: E. Michael Fincke (third flight) Mission Specialist: E. Michael Fincke (third flight) Mission Specialist: E. Michael Fincke (third flight) Mission Specialist: Roberto Vittori, European Space Mission Specialist: Roberto Vittori, European Space Mission Specialist: Roberto Vittori, European Space Agency (ESA) (third flight) Agency (ESA) (third flight) Agency (ESA) (third flight) Mission Specialist: Andrew J. Feustel (second flight) Mission Specialist: Andrew J. Feustel (second flight) Mission Specialist: Andrew J. Feustel (second flight) Mission Specialist: Gregory E. Chamitoff (third flight) Mission Specialist: Gregory E. Chamitoff (third flight) Mission Specialist: Gregory E. Chamitoff (third flight) Payload: ISS Assembly Flight ULF6; ExPRESS Logistics Payload: ISS Assembly Flight ULF6; ExPRESS Logistics Payload: ISS Assembly Flight ULF6; ExPRESS Logistics Carrier 3 (ELC3); Alpha Magnetic Spectrometer Carrier 3 (ELC3); Alpha Magnetic Spectrometer Carrier 3 (ELC3); Alpha Magnetic Spectrometer (AMS) (AMS) (AMS) Projected launch date is July 2010, with Endeavour Projected launch date is July 2010, with Endeavour Projected launch date is July 2010, with Endeavour (OV-105) in its 25th and fi nal fl ight (OV-105) in its 25th and fi nal fl ight (OV-105) in its 25th and fi nal fl ight Of Note: Commander Mark Kelly’s identical twin brother, Of Note: Commander Mark Kelly’s identical twin brother, Of Note: Commander Mark Kelly’s identical twin brother, Scott Kelly, is scheduled to arrive at the space sta- Scott Kelly, is scheduled to arrive at the space sta- Scott Kelly, is scheduled to arrive at the space sta- tion in October 2010 to serve as ISS Expedition 25 tion in October 2010 to serve as ISS Expedition 25 tion in October 2010 to serve as ISS Expedition 25 flight engineer and commander of Expedition 26. flight engineer and commander of Expedition 26. flight engineer and commander of Expedition 26. Because of the fluidity of launch schedules, the two Because of the fluidity of launch schedules, the two Because of the fluidity of launch schedules, the two may meet in space. may meet in space. may meet in space.

STS-133 Flight Crew STS-133 Flight Crew STS-133 Flight Crew

Commander: Steven W. Lindsey (fifth flight) Commander: Steven W. Lindsey (fifth flight) Commander: Steven W. Lindsey (fifth flight) Pilot: Eric A. Boe (second flight) Pilot: Eric A. Boe (second flight) Pilot: Eric A. Boe (second flight) Mission Specialist: Benjamin Alvin Drew Jr. (second flight) Mission Specialist: Benjamin Alvin Drew Jr. (second flight) Mission Specialist: Benjamin Alvin Drew Jr. (second flight) Mission Specialist: Michael R. Barratt (second flight) Mission Specialist: Michael R. Barratt (second flight) Mission Specialist: Michael R. Barratt (second flight) Mission Specialist: Timothy L. Kopra (third flight) Mission Specialist: Timothy L. Kopra (third flight) Mission Specialist: Timothy L. Kopra (third flight) Mission Specialist: Nicole P. Stott (third flight) Mission Specialist: Nicole P. Stott (third flight) Mission Specialist: Nicole P. Stott (third flight) Payload: ISS Assembly Flight ULF5; ExPRESS Logistics Payload: ISS Assembly Flight ULF5; ExPRESS Logistics Payload: ISS Assembly Flight ULF5; ExPRESS Logistics Carrier 4 (ELC4); Permanent Logistics Module (PLM) Carrier 4 (ELC4); Permanent Logistics Module (PLM) Carrier 4 (ELC4); Permanent Logistics Module (PLM) Projected launch date is September 2010, with Projected launch date is September 2010, with Projected launch date is September 2010, with Discovery (OV-103) in its 39th and fi nal fl ight Discovery (OV-103) in its 39th and fi nal fl ight Discovery (OV-103) in its 39th and fi nal fl ight Of Note: Last flight of the Space Shuttle Program Of Note: Last flight of the Space Shuttle Program Of Note: Last flight of the Space Shuttle Program

G-2 G-2 G-2

Photos courtesy of NASA and ESA Photos courtesy of NASA and ESA Photos courtesy of NASA and ESA

The STS-130 Reporter’s Space Flight Notepad The STS-130 Reporter’s Space Flight Notepad The STS-130 Reporter’s Space Flight Notepad was produced by Creative Services in was produced by Creative Services in was produced by Creative Services in Huntington Beach, Calif. Huntington Beach, Calif. Huntington Beach, Calif.

Writer/Editor: Bernadette Coleman Writer/Editor: Bernadette Coleman Writer/Editor: Bernadette Coleman Layout: Christine Guerrero Layout: Christine Guerrero Layout: Christine Guerrero Graphics: Reginald Morris Graphics: Reginald Morris Graphics: Reginald Morris

Boeing in Space Boeing in Space Boeing in Space

The Boeing Company’s human space fl ight legacy The Boeing Company’s human space fl ight legacy The Boeing Company’s human space fl ight legacy spans more than 50 years, including development of spans more than 50 years, including development of spans more than 50 years, including development of the space shuttle, International Space Station, and the space shuttle, International Space Station, and the space shuttle, International Space Station, and the contract to produce the upper stage of the Ares I the contract to produce the upper stage of the Ares I the contract to produce the upper stage of the Ares I crew launch vehicle, the spacecraft that will propel crew launch vehicle, the spacecraft that will propel crew launch vehicle, the spacecraft that will propel the Orion crew vehicle to the moon. the Orion crew vehicle to the moon. the Orion crew vehicle to the moon.

Boeing maintains its tradition today by integrating Boeing maintains its tradition today by integrating Boeing maintains its tradition today by integrating space shuttle systems and payloads and providing space shuttle systems and payloads and providing space shuttle systems and payloads and providing orbiter engineering support. Boeing also acts as the orbiter engineering support. Boeing also acts as the orbiter engineering support. Boeing also acts as the lead contractor for the ISS—planet Earth’s perma- lead contractor for the ISS—planet Earth’s perma- lead contractor for the ISS—planet Earth’s perma- nent orbital outpost. nent orbital outpost. nent orbital outpost.

With an eye on the future, Boeing engineers and With an eye on the future, Boeing engineers and With an eye on the future, Boeing engineers and scientists are developing technologies to return to scientists are developing technologies to return to scientists are developing technologies to return to the moon and explore Mars someday, while increas- the moon and explore Mars someday, while increas- the moon and explore Mars someday, while increas- ing human presence in space. ing human presence in space. ing human presence in space.

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