National Aeronautics and Space Administration

SPACE SHUTTLE MISSION STS-133 PRESS KIT/November 2010

The Final Flight of Discovery

This press kit is under revision. An updated version will be posted at a later date.

www.nasa.gov

CONTENTS

Section Page

MISSION OVERVIEW ...... 1

TIMELINE OVERVIEW ...... 9

MISSION PROFILE ...... 11

MISSION OBJECTIVES ...... 13

MISSION PERSONNEL ...... 15

DISCOVERY CREW ...... 17

PAYLOAD OVERVIEW ...... 25 PERMANENT MULTIPURPOSE MODULE ...... 25 EXPRESS LOGISTICS CARRIER 4 ...... 31 ROBONAUT 2 ...... 34

RENDEZVOUS & DOCKING ...... 37 UNDOCKING, SEPARATION AND DEPARTURE ...... 38

SPACEWALKS ...... 39

EXPERIMENTS ...... 45 SHORT-DURATION EXPERIMENTS TO BE PERFORMED ON STS-133 ...... 45 RESEARCH SAMPLES/HARDWARE TO BE DELIVERED TO STATION ON DISCOVERY ...... 47 RESEARCH SAMPLES/HARDWARE TO BE RETURNED ON DISCOVERY ...... 51 SPACE SHUTTLE DETAILED TEST OBJECTIVES (DTO) AND DETAILED SUPPLEMENTARY OBJECTIVES (DSO) ...... 53

HISTORY OF SPACE SHUTTLE DISCOVERY ...... 57

SHUTTLE REFERENCE DATA ...... 61

NOVEMBER 2010 CONTENTS i

Section Page

LAUNCH AND LANDING ...... 79 LAUNCH ...... 79 ABORT TO ORBIT ...... 79 TRANSATLANTIC ABORT LANDING ...... 79 RETURN TO LAUNCH SITE ...... 79 ABORT ONCE AROUND ...... 79 LANDING ...... 79

ACRONYMS AND ABBREVIATIONS ...... 81

MEDIA ASSISTANCE ...... 95

PUBLIC AFFAIRS CONTACTS ...... 97

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MISSION OVERVIEW

At NASA’s Kennedy Space Center in Florida, space shuttle Discovery is poised for the STS-133 launch from Launch Pad 39A following the roughly six-hour journey, known as “rollout,” from the Vehicle Assembly Building to the pad. Image credit: NASA/Jim Grossmann

As space shuttle Discovery heads to the 4:40 p.m. EDT on Monday, Nov. 1. The flight is International Space Station on its final mission, designated Utilization and Logistics Flight 5 it will be taking with it two key components – (ULF5), in the assembly sequence of the space the Italian-built Permanent Multipurpose station. Module (PMM) and Express Logistics Carrier 4 (ELC4) – that will provide spare parts and The commander for Discovery’s final flight is storage capacity to the orbiting complex. veteran astronaut Steve Lindsey (Colonel, Discovery also will deliver Robonaut 2, which USAF, Retired). He will be joined by Pilot will become the first humanoid robot in space. Eric Boe (Colonel, USAF) and Mission Specialists Timothy Kopra (Colonel, U.S. The 39th flight of NASA’s most flown shuttle is Army), Dr. Michael Barratt, Nicole Stott and scheduled to last 11 days, beginning at Alvin Drew (Colonel, USAF Retired).

NOVEMBER 2010 MISSION OVERVIEW 1

While seated at the commander’s station, NASA astronaut Steve Lindsey, STS-133 commander, participates in a post insertion/deorbit training session in the crew compartment trainer in the Space Vehicle Mock-up Facility at NASA’s Johnson Space Center. Lindsey is wearing a training version of his shuttle launch and entry suit.

Lindsey has flown four times before, including Expedition 20 and Stott served as a member of twice on Space Shuttle Discovery. He was pilot Expeditions 20 and 21, all in 2009. on STS-95, where Senator John Glenn served as a payload specialist. Lindsey also commanded Discovery will spend two days heading toward STS-121, a return to flight mission in July 2006. its rendezvous with the International Space Station. On the second day of the flight, the Boe previously served as the pilot of STS-126 in crew will perform the standard scan of the November 2008, which delivered a number of shuttle’s thermal protection system using the supplies and new equipment to the station. orbiter boom sensor system attached to the end Drew flew on STS-118 in August 2007, which of Discovery’s robotic arm. While the delivered a piece of the station’s truss structure. inspection is underway, Kopra, Drew and Stott Kopra, Barratt and Stott are all previous will work on preparing the spacesuits onboard residents of the International Space Station. the shuttle that will be transferred to the station Barratt served as a member of Expeditions 19 after docking and will be used during the and 20, Kopra served as a member of mission’s two spacewalks.

2 MISSION OVERVIEW NOVEMBER 2010

NASA astronauts Michael Barratt (foreground), Alvin Drew (left background) and Tim Kopra, all STS-133 mission specialists, participate in a training session in an International Space Station mock-up/trainer in the Space Vehicle Mock-up Facility at NASA’s Johnson Space Center.

On the third day of the flight, Discovery will starboard truss, right next to where the Alpha approach and dock with the space station. Magnetic Spectrometer will be installed on After the hatches are opened between the two STS-134. That mission also will deliver ELC3, spacecraft, both crews will begin working on which will be the final logistics carrier installed transferring items between the two vehicles. on the station. It will be positioned on the Before the end of the day, they will use the upper outboard attachment point on the port station’s robotic arm to retrieve ELC4 from side. inside the shuttle’s payload bay and install it in the lower inboard position on the starboard Flight day 4 will be focused on more transfer side of the station’s truss structure. The cargo work, as well as preparations by Kopra and carrier weighs 8,235 pounds. ELC1 and 2 were Drew for their spacewalk the next day. Both placed on the on the station’s truss structure crews will walk through the choreography of during STS-129. ELC1 is mounted on the lower the spacewalk, and both Kopra and Drew will inboard position on the port side of the station. spend the night camped out inside the Quest ELC2 is on the upper outboard side of the airlock.

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The main activity for flight day 5 will be the camera wedge, which will allow access to the spacewalk itself. While outside, Kopra and external camera that is mounted on the Drew will install a power extension cable that starboard side of the station. This camera is could be used between Unity and Tranquility in located very close to where ELC4 will be the event Tranquility ever loses power. It needs installed, and to allow enough clearance for to be installed before the PMM is secured in future spare parts to be loaded onto the carrier, place because of access to the work area. They this wedge will tilt the camera stanchion out of will move the failed ammonia pump that the way. Also, Kopra and Drew will install two Doug Wheelock and Tracy Caldwell Dyson rail stubs, which are small extensions on the removed during Expedition 24 from its end of the station’s mobile transporter rail. temporary stowage location on the station’s These stubs will allow the mobile transporter to mobile base structure to External Stowage travel the entire length of the rail with the crew Platform 2, which is on the side of the Quest and equipment translation aid (CETA) cart airlock. The two spacewalkers will install a attached, and reach all of the work sites.

NASA astronaut Alvin Drew, STS-133 mission specialist, participates in a spacesuit fit check in the Space Station Airlock Test Article in the Crew Systems Laboratory at NASA’s Johnson Space Center. Astronaut Nicole Stott, mission specialist, assists Drew.

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For both spacewalks, Kopra, who has Unity node. The PMM will carry 14 racks to the conducted one spacewalk during the STS-127 station – an experiment rack, six resupply mission at the station, will be designed stowage platforms, five resupply stowage racks extravehicular crew member 1 (EV1), and will and two integrated stowage platforms. wear the suit bearing red stripes. Drew, who will be making his first two spacewalks on STS- Among the items tucked away inside the PMM, 133, will be extravehicular crew member 2 is Robonaut 2, known as R2. Although its (EV2) and will wear the unmarked suit. primary job for now is demonstrating to engineers how dexterous robots behave in Flight day 6 will be focused on the installation space, the hope is that, through upgrades and of the PMM. The PMM is about the same size advancements, it could one day venture outside as the Columbus laboratory and is also known the station to help spacewalkers make repairs as Leonardo, one of the multi-purpose logistics or additions to the station or perform scientific modules. It was modified to become a work. Once R2 is unpacked, likely several permanent module attached to the International months after it arrives, it will be initially Space Station. Once in orbit, the PMM will operated inside the Destiny laboratory for offer 2,472 additional cubic feet of pressurized operational testing, but over time, both its volume for stowage and for scientific use. It territory and its applications could expand. will be installed on the earth-facing side of the There are no plans to return R2 to Earth.

NASA astronaut Michael Barratt, STS-133 mission specialist, shakes hands with Robonaut 2 (R2) during media day in the Space Vehicle Mock-up Facility at NASA’s Johnson Space Center. Ron Diftler, NASA Robonaut project manager, is at left.

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Flight day 7 will include the second and final from the Tranquility node. Also, the spacewalk of the mission. Drew and Kopra will spacewalkers will troubleshoot the radiator be the spacewalkers once again and will focus grapple stowage beams located on the port side on removing thermal covers from the express of the station. This is being done in advance of pallet carrier assembly on ELC4. Kopra will some spare radiator panels that will arrive at remove a light-weight adapter plate assembly the station in the future. from the Columbus module and will install a new version of that payload bracket. Drew will Flight days 8 and 9 will be spent completing reconfigure the starboard CETA cart and will transfer work between Discovery and the space install a new light fixture on it. Kopra will station. The crews will also enjoy some install a new camera pan and tilt unit on the off-duty time prior to Discovery’s undocking, Dextre robot and will remove thermal covers which will take place on flight day 10.

Attired in a training version of his shuttle launch and entry suit, NASA astronaut Eric Boe, STS-133 pilot, occupies the pilot’s seat during a simulation exercise in the motion-base shuttle mission simulator in the Jake Garn Simulation and Training Facility at NASA’s Johnson Space Center.

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Once Discovery undocks from the station, Boe Flight day 11 will be spent checking out the will fly the shuttle in a final victory lap around reaction control system (RCS) jets and the flight the International Space Station complex. The control surfaces. Both of these systems will be shuttle crew will take detailed photographs of put through their paces to ensure that they are the external structure of the station, which ready to support Discovery’s landing. The RCS serves as important documentation for the jets will be used during the early part of entry, ground teams in Houston to monitor the up until the atmosphere builds up enough for orbiting laboratory. Once the loop of the the flight control surfaces to take over and steer station is finished, Discovery will fire its the shuttle toward the runway. engines to take it away from the vicinity of the station. That same day, the crew will complete Discovery is scheduled to land on flight day 12 the late inspection of the shuttle’s heat shield to at mid-morning at the Kennedy Space Center in ensure that nothing was damaged during the Florida. At the time of its landing, Discovery docked phase of the mission. will have traveled almost 143 million miles over the course of 26 years in service to the nation and the world.

Space Shuttle Discovery lands on Runway 33 at the Shuttle Landing Facility at NASA’s Kennedy Space Center in Florida at 9:08 a.m. (EDT) on April 20, 2010, completing the 15-day STS-131 mission to the International Space Station.

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TIMELINE OVERVIEW

Flight Day 1 • Hatch opening and welcoming

• Launch • Canadarm2 grapple of Express Logistics Carrier 4 (ELC4) cargo pallet, handoff to • Payload bay door opening shuttle robotic arm, and handoff back to • Ku-band antenna deployment Canadarm2 for installation on the starboard 3 lower inboard attachment system • Shuttle robotic arm activation and payload bay survey Flight Day 4

• Umbilical well and handheld external tank • Cargo transfer photo and TV downlink • OBSS handoff from Canadarm2 to shuttle Flight Day 2 robotic arm • • Discovery’s thermal protection system Spacewalk tool preparation survey with shuttle robotic arm/orbiter • Spacewalk 1 preparations by Kopra and boom sensor system (OBSS) Drew • Extravehicular mobility unit, or spacesuit, • Spacewalk 1 procedure review checkout • Spacewalk 1 campout by Kopra and Drew in • Centerline camera installation the Quest airlock • Orbiter docking system ring extension Flight Day 5 • Orbital maneuvering system pod survey • Spacewalk 1 by Kopra and Drew • Rendezvous tools checkout (J612 power extension cable installation from Unity to Tranquility, transfer of failed pump Flight Day 3 module from the payload attachment • Rendezvous with the International Space bracket on the mobile base system to Station external stowage platform 2, installation of a wedge for camera port 3 and installation of • Rendezvous pitch maneuver photography of starboard crew equipment and translation Discovery’s thermal protection system by aid (CETA) cart rail stubs) Expedition 25 crew members Fyodor Yurchikhin and Shannon Walker Flight Day 6 • • Docking to Harmony/pressurized mating Installation of the Permanent Multipurpose adapter 2 Module (PMM) to the nadir, or Earth-facing, port of Unity

NOVEMBER 2010 TIMELINE OVERVIEW 9

• Focused inspection of Discovery’s thermal • Farewells and hatch closure protection heat shield, if required • Centerline camera installation • Spacewalk 2 preparations by Kopra and Flight Day 10 Drew • Discovery’s final undocking from station and • Spacewalk 2 procedure review fly-around • Spacewalk 2 campout by Kopra and Drew in • Final separation from the station the Quest airlock • Flight Day 7 OBSS late inspection of Discovery’s thermal heat shield • PMM ingress and internal outfitting • OBSS berth • Spacewalk 2 by Kopra and Drew (removal of Flight Day 11 thermal insulation from the ELC4, installation of CETA lights, troubleshooting • Cabin stowage of the port 1 truss radiator stowage beam • bracket, removal and replacement of a cargo Flight control system checkout adapter plate on Columbus, installation of a • Reaction control system hot-fire test pan and tilt unit on a camera on Dextre and • removal of thermal covers) Deorbit preparation briefing • Flight Day 8 Ku-band antenna stowage

• Cargo transfer to station from the PMM Flight Day 12 • • Crew off duty time Deorbit preparations • Flight Day 9 Payload bay door closing • • Reconfiguration of spacewalk equipment Deorbit burn • • Joint crew news conference Discovery’s final landing at KSC

• Crew off-duty time

• Rendezvous tools checkout

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MISSION PROFILE

CREW Space Shuttle Main Engines:

Commander: Steve Lindsey SSME 1: 2044 Pilot: Eric Boe SSME 2: 2048 Mission Specialist 1: Alvin Drew SSME 3: 2058 Mission Specialist 2: Tim Kopra External Tank: ET-137 Mission Specialist 3: Michael Barratt SRB Set: BI-144 Mission Specialist 4: Nicole Stott RSRM Set: RSRM-112

LAUNCH SHUTTLE ABORTS

Orbiter: Discovery (OV-103) Abort Landing Sites Launch Site: Kennedy Space Center, RTLS: Kennedy Space Center Shuttle Launch Pad 39A Landing Facility Launch Date: Nov. 1, 2010 TAL: Primary – Zaragoza, Spain Launch Time: 4:40 p.m. EDT (preferred Alternates – Morón, Spain and in-plane launch time for Istres, France Nov. 1) AOA: Primary – Kennedy Space Center Launch Window: 10 Minutes Shuttle Landing Facility Altitude: 122 Nautical Miles Alternate – White Sands Space (140 Miles) orbital insertion; Harbor 190 nautical miles (218 statute miles) rendezvous LANDING Inclination: 51.6 degrees Duration: 10 days, 18 hours, 59 minutes Landing Date: Nov. 12, 2010 Landing Time: 10:39 a.m. EST VEHICLE DATA Primary landing Site: Kennedy Space Center Shuttle Liftoff Weight: 4,525,220 PAYLOADS pounds Orbiter/Payload Liftoff Weight: 268,620 Express Logistics Carrier 4 (ELC4) pounds Permanent Multipurpose Module (PMM) Orbiter/Payload Landing Weight: 204,736 pounds Software Version: OI-34

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MISSION OBJECTIVES

1. Rendezvous and dock space shuttle − Activate PMM systems. Discovery to the International Space Station − pressurized mating adapter 2 and perform Ingress PMM. mandatory safety briefing for all crew − Install one portable fire extinguisher members. and one portable breathing apparatus in PMM. 2. Robotically install Express Logistics Carrier 4 (ELC4) to starboard three truss lower 9. Support communication requirements inboard common attach site. (voice and video) for Russian spacewalk prep. (A Russian spacewalk is planned to 3. Robotically install Permanent Multipurpose follow soon after Discovery undock and this Module (PMM) to Unity node nadir or is prep for that spacewalk.) Earth-facing port. 10. Perform daily space station payload status 4. PMM activities: Perform minimal checks, as required. activation and checkout to preserve module and cargo (if only a short time allowed for 11. Transfer oxygen from the orbiter to the PMM activation, do enough to ensure the station airlock high pressure gas tanks; PMM survival. However, nominal timeline 25 pounds minimum. will allow full activation). Perform passive common berthing mechanism sealing 12. Transfer nitrogen from the orbiter to the surface inspection. station airlock high pressure gas tanks; 25 pounds minimum. 5. Activate ELC4. 13. Transfer remaining cargo items per flight 6. Transfer and stow critical items per ULF5 TPL. Utilization and Logistics Flight 5 (ULF5) transfer priorities list (TPL). 14. Perform daily middeck activities to support payloads (status checks). 7. Complete spacewalk tasks to support station operations. There are also several 15. Perform space station payload research other spacewalk tasks deemed to fit within operations tasks. the existing spacewalk timelines; however, they may be deferred if the spacewalk is 16. Complete camera port 3 (CP3) camera behind schedule. The spacewalk will not be calibration, checkout and survey after the extended to complete these tasks. CP3 wedge is installed (spacewalk task), and downlink data for analysis. 8. Activate and check out PMM (this is the nominally planned activation).

NOVEMBER 2010 MISSION OBJECTIVES 13

17. Perform intravehicular activity tasks: − Perform SDTO 13005-U, ISS structural life validation and extension during − Install recycle filter tank assembly. ULF5 orbiter undocking (IWIS highly desired). − Remove and replace Tranquility node atmosphere revitalization rack carbon 24. Perform payloads of opportunity (not dioxide removal assembly bed. required during docked ops) if propellant available. 18. Transfer water from orbiter to space station per flight ULF5 TPL. − Ram Burn Observations 2 (RAMBO-2).

19. Reboost the space station with the orbiter if − Maui Analysis of Upper Atmospheric mission resources allow and are consistent Injections (MAUI). with station trajectory analysis and planning. − Shuttle Exhaust Ion Turbulence Experiments (SEITE). 20. Perform imagery survey of the space station − exterior during orbiter fly-around after Shuttle Ionospheric Modification with undock. Pulsed Local Exhaust (SIMPLEX). 25. Perform program-approved spacewalk get- 21. Perform checkout of ELC4. ahead tasks. These tasks do not fit in the 22. Perform Developmental Test Objective existing spacewalk timelines; however, the (DTO) 701b (DragonEye Flash Light spacewalk team will be trained and ready to Intensification Detection and Ranging). perform them should the opportunity arise. The spacewalk operations team in mission 23. Perform structural SDTOs (Station control has the flexibility to select the tasks Developmental Test Objective) as follows: to be completed based on efficiencies gained in performing the already scheduled − Perform SDTO 13005-U, ISS structural required tasks. life validation and extension, during ULF5 orbiter docking. 26. Perform program approved interior get- ahead tasks. These tasks do not fit in the − Perform SDTO 13005-U, ISS structural existing timelines; however, the operations life validation and extension, during team and crew will be trained and ready to PMM installation (ISS wireless perform should the opportunity arise. instrumentation system (IWIS)) required. 27. Perform imagery of space station’s Russian segment exterior for historical − Perform SDTO 13005-U, ISS structural documentation. life validation and extension, during ULF5 mated reboost (IWIS required).

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MISSION PERSONNEL

KEY CONSOLE POSITIONS FOR STS-133

Flt. Director CAPCOM PAO

Ascent Richard Jones Charlie Hobaugh Josh Byerly Steve Frick (Wx)

Orbit 1 (Lead) Bryan Lunney Steve Robinson Josh Byerly

Orbit 2 Ginger Kerrick Megan McArthur Pat Ryan

Planning Rick LaBrode Mike Massimino Brandi Dean

Entry Tony Ceccacci Charlie Hobaugh Josh Byerly Terry Virts (Wx)

Shuttle Team 4 Paul Dye N/A N/A

STATION Orbit 1 David Korth Hal Getzelman N/A

STATION Orbit 2 (Lead) Royce Renfrew Stan Love N/A

STATION Orbit 3 Chris Edelen Kathy Bolt N/A

Station Team 4 Kwatsi Alibaruho

JSC PAO Representative at KSC for Launch – Lynnette Madison

KSC Launch Commentator – George Diller

KSC Launch Director – Mike Leinbach

NASA Launch Test Director – Steve Payne

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16 MISSION PERSONNEL NOVEMBER 2010

DISCOVERY CREW

The STS-133 mission patch is based upon flame as if it is just beginning a mission. sketches from the late artist Robert McCall; they However it is just the orbiter, without boosters were the final creations of his long and or an external tank, as it would be at mission’s prodigious career. In the foreground, a solitary end. This is to signify Discovery’s completion orbiter ascends into a dark blue sky above a of its operational life and the beginning of its roiling fiery plume. A spray of stars surrounds new role as a symbol of NASA’s and the the orbiter and a top-lit crescent forms the nation’s proud legacy in human spaceflight. background behind the ascent. The mission number, STS-133, is emblazoned on the patch Short biographical sketches of the crew follow center, and crew members’ names are listed on with more detailed biographies available at: a sky-blue border around the scene. The shuttle http://www.jsc.nasa.gov/bios/. Discovery is depicted ascending on a plume of

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The STS-133 crew members take a brief break for a portrait in the Space Vehicle Mock-up Facility at NASA’s Johnson Space Center. From the left are NASA astronauts Tim Kopra and Alvin Drew, both mission specialists; Eric Boe, pilot; Steve Lindsey, commander; Michael Barratt and Nicole Stott, both mission specialists.

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CREW BIOGRAPHIES

Steve Lindsey

Retired U.S. Air Force Colonel Steve Lindsey, cockpit council and chief of International Space 50, will serve as commander of STS-133. In his Station operations. His most recent position role as commander, he will have overall was chief of the astronaut corps where he was responsibility for the mission and will ensure responsible for the mission preparation that all objectives are executed safely. activities of all space shuttle and International Space Station crews and their support Lindsey has performed several technical duties personnel. that include working as the shuttle landing and rollout representative, deputy for shuttle A veteran of four spaceflights, he has logged operations, co-chairman of the space shuttle more than 1,203 hours in space.

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Eric Boe

Eric Boe, 46, a colonel in the U.S. Air Force, will operations branch and space shuttle branch. serve as pilot of STS-133. For one year he served as NASA’s director of operations at the Gagarin Cosmonaut Training Selected by NASA in 2000, he completed two Center in Star City, Russia. years of training and evaluation, then was assigned technical duties in the astronaut office Boe first served as a pilot on STS-126, a 15-day advanced vehicles branch, space station mission in November 2008.

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Alvin Drew

In his second trip to space, Alvin Drew, 47, a Cosmonaut Training Center in Star City, retired colonel in the U.S. Air Force, will serve Russia. as a mission specialist on STS-133. Selected by NASA in 2000 and after completing astronaut A command pilot, he has more than 25 years of training, he was initially assigned technical experience and 3,500 hours of flying duties in the astronaut office space station 30 different types of aircraft. The Washington, operations branch. Drew then served as D.C., native logged more than 305 hours in NASA’s director of operations at the Gagarin space during the STS-118 space shuttle mission in August 2007.

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Tim Kopra

Veteran of one long duration mission, operations and space station hardware testing. Tim Kopra, 47, also will serve as a mission Following initial astronaut training, he served specialist for the mission. in the space station branch of the astronaut office. His first mission was as a flight engineer Before his selection to the astronaut corps in during Expedition 20 in 2009. Kopra logged 2000, Kopra worked as a vehicle integration test two months in space, including one spacewalk engineer where he primarily served as an during STS-127, the mission that brought him engineering liaison for space shuttle launch to the station.

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Michael Barratt

Dr. Michael Barratt, 51, will serve as a mission served as lead crew surgeon for first expedition specialist on the STS-133 crew. crew to the space station from July 1998 until selected as an astronaut candidate in 2000. Barratt, a board certified physician in internal and aerospace medicine, began his career in the He served numerous technical roles before space program as a project physician with training for his first mission as a flight engineer KRUG Life Sciences in 1991, and joined NASA on Expeditions 19 and 20 in 2009. During that as a flight surgeon in 1992. From July 1995 mission, he acquired 199 days of spaceflight through July 1998, he served as medical experience. operations lead for the space station and then

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Nicole Stott

Nicole Stott, 47, also joined the astronaut ranks the aircraft operations division, where she after working at NASA. Stott initially joined served as a flight simulation engineer on the NASA at the Kennedy Space Center in Florida, shuttle training aircraft. serving numerous roles including vehicle operations engineer, NASA convoy Stott, also selected as an astronaut in 2000, flew commander, shuttle flow director for space her first mission in 2009 as a flight engineer for shuttle Endeavour and orbiter project engineer the Expedition 20 and 21 crews, logging 91 days for space shuttle Columbia. In 1998, she joined in space. Stott will serve as a mission specialist the Johnson Space Center team as a member of on the STS-133 crew.

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PAYLOAD OVERVIEW

This graphic depicts the space shuttle Discovery’s payload bay for STS-133, which includes the Permanent Multipurpose Module and the Express Logistics Carrier 4. The total payload weight, not counting the middeck, is 22,160 pounds.

PERMANENT MULTIPURPOSE MODULE To transform an existing logistics carrier used for 10 years into a permanent module able to The Permanent Multipurpose Module (PMM) is stay an additional 10 years in orbit, a large, reusable pressurized element, carried in modifications consisted of the following: the space shuttle’s cargo bay, originally used to ferry cargo back and forth to the station. For • Enhance the module shielding with an STS-133, the PMM, known as Leonardo, was improved micrometeoroid debris protective modified to become a permanent module shield design to satisfy the new penetration attached to the International Space Station. requirements. Once in orbit, the PMM will offer • 2,472 additional cubic feet of pressurized Provide the in-orbit maintenance capability volume for storage and for scientific use. The by changing the internal harness routing module is carried in the cargo bay of Discovery and brackets layout to allow the crew and will be connected to the Unity node on the accessibility to the internal equipment. station.

NOVEMBER 2010 PAYLOAD OVERVIEW 25

The PMM is 21 feet long and 15 feet in diameter – the same size as the European Space Agency’s Columbus module.

• Provide easy interfaces for future On the STS-133 mission, the PMM will carry exploitation of the retained resources. 14 racks to the station – one experiment rack, six resupply stowage platforms (RSPs), • Provide a certified life extension for all five resupply stowage racks (RSRs), and equipments and subsystems. two integrated stowage platforms (ISPs). • Developed a software update to eliminate The experiment rack carried in the PMM is the faulty alarms. Express Rack 8. The Italian Space Agency contracted with Thales Alenia Space, which also designed and PMM Specifications built the three multi-purpose logistic modules, Dimensions: Length: 21 feet to make the modifications. This module flew Diameter: 15 feet seven times as Leonardo, the multipurpose Payload Mass (launch): 27,160 pounds logistics module. As the PMM module, this Empty Weight: 9,672 pounds will be its final flight and the last pressurized element to be added to the U.S. operating segment (USOS) of the station.

26 PAYLOAD OVERVIEW NOVEMBER 2010

In the Space Station Processing Facility at NASA’s Kennedy Space Center in Florida, a technician installs multilayer insulation on the meteoroids and debris protective shield of the Permanent Multipurpose Module. The reflective silver mesh is Mylar, which is aluminized to protect hardware aboard the International Space Station from solar thermal radiation.

Express Rack 8 quick, simple integration of multiple payloads aboard the station. The system is composed of Express rack 8 is a multi-purpose payload rack elements that remain on the station and system that stores and supports experiments elements that travel back and forth between the aboard the International Space Station. Express station and Earth via the space shuttle. Express stands for Expedite the Processing of racks remain in space continually. Experiments Experiments to the Space Station. The Express are replaced in the Express racks as needed, rack system supports science experiments in remaining on the station for periods ranging any discipline by providing structural from three months to several years, depending interfaces, power, data, cooling, water and on the experiment’s time requirements. other items needed to operate science experiments in space. Payloads within an Express rack can operate independently of each other, allowing for With standardized hardware interfaces and a differences in temperature, power levels and streamlined approach, the Express rack enables schedules. The Express rack provides stowage,

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The following spare parts are also being carried in the PMM:

Common Cabin Air Assembly Heat Exchanger

The common cabin air assembly (CCAA) heat exchanger (HX) is a condensing heat exchanger – an integral part of the temperature and humidity control (THC) subsystem. The CCAA HX is used to automatically control temperature and humidity within the USOS according to the needs of the crew. The condensate is collected and sent to the condensate bus, where the water is reclaimed, and sent on to be processed into potable water. The CCAA HX is roughly 125 pounds when filled with water. The dimensions, minus hoses, are approximately 34.8 inches by 21.4 inches by 17.5 inches. The unit is manufactured by Hamilton Sundstrand, Windsor Locks, Conn. The CCAA HX is configured to be used in the Harmony node. power, data, command and control, video, water cooling, air cooling, vacuum exhaust and nitrogen supply to payloads. Each Express rack is housed in an international standard payload rack (ISPR), a refrigerator-sized container that serves as the rack’s exterior shell.

Experiments contained within EXPRESS racks may be controlled by the station crew or remotely by the payload rack officer (PRO) on duty at the Payload Operations and Integration Center at Marshall Space Flight Center in Huntsville, Ala. Linked by computer to all payload racks aboard the station, the PRO routinely checks rack integrity, temperature control and proper working conditions for station research payloads.

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Boeing is responsible for sustaining engineering assembly is completely enclosed in thermal in the USOS. The hardware is sustained by the insulation. The PPA weighs 191 pounds with Boeing environmental controls and life support the ITCS fluid fill. It measures 29.64 inches by (ECLS) and THC team in Houston. This team 18.63 inches by 17.75 inches. The PPAs are manages and maintains all ECLS hardware and manufactured by Honeywell, Inc., Torrance, provides technical support to the station Calif. operations team in mission control. The hardware is sustained by the Boeing Active Pump Package Assembly Thermal Control System (ATCS) team in Houston. This team manages and maintains all The pump package assembly (PPA) is being ATCS hardware and provides technical support delivered to serve as a second available spare to the station operations team in mission on board the station. It provides the motive control. force for circulating coolant fluid throughout the Internal Thermal Control System (ITCS) Inlet loops. The PPAs are installed in both the low- and moderate-temperature loops of the Destiny The inlet is a large cabin fan and is used as an laboratory, Harmony node and Tranquility integral part of the temperature and humidity node. control (THC) subsystem. The cabin fan provides intra-module ventilation in all USOS It provides for coolant expansion/contraction modules. It is a multispeed, acoustically due to thermal excursions and provides a treated fan that maintains proper mixing of the reservoir for inadvertent coolant spill make-up. cabin atmosphere. This Inlet ORU is being The bolted assembly consists of a central launched as a spare to keep on board. The inlet manifold, centrifugal pump driven with a weighs 58.81 pounds and the dimensions are brushless DC motor and a firmware controller, approximately 17.5 inches by 21 inches by a noncondensable gas trap, various water lines, 24 inches. It is manufactured by Hamilton gas trap differential pressure sensor, flow Sundstrand, Windsor Locks, Conn. The meter, accumulator/reservoir, with coolant hardware is sustained by the Boeing ELCS, quantity sensor, filter (with isolation valves), temperature, humidity controls, and ventilation pump outlet temperature sensor, pump inlet pressure sensor, filter delta pressure sensor, and a pump delta pressure sensor. The

NOVEMBER 2010 PAYLOAD OVERVIEW 29

team in Houston. This team manages and 19.38 inches. The unit is manufactured by maintains all ECLS hardware and provides Hamilton Sundstrand, Windsor Locks, Conn. technical support to the station operations team The WPA water storage tank is configured to be in mission control. used in the Tranquility node to support six crew members on the station. Water Processor Assembly Water Storage Tank Boeing is responsible for sustaining engineering in the USOS. The hardware is sustained by the The water processor assembly (WPA) water Boeing ECLS and water evaluation team in storage tank detects conductivity and gas Houston. This team manages and maintains all content of the water that has been produced by ECLS hardware and provides technical support the WPA. The tank either provides storage of to the station operations team in mission up to 125 pounds of acceptable water or rejects control. the water for reprocessing. It consists of a bellows tank with quantity sensors, solenoid Water Processor Assembly Waste Water Tank valves, and sensors for determining the water’s acceptability for use. A conductivity sensor The WPA waste water tank provides up to and a gas sensor are used to check the product 100 pounds of storage of the condensate water. Acceptable water is passed to the tank collected in the waste water bus from the and stored before it is distributed to the potable station and urine distillate produced by the water bus, while out-of-specification water is urine processor assembly before it is processed redirected back through the WPA for by the WPA. It consists of a bellows tank with reprocessing. quantity sensors and solenoid valves to allow isolation of the tank when it is full. The water storage tank weighs 154 pounds when empty and is on the bottom shelf on the The waste water tank weighs 230 pounds when right side of water recovery system 1 rack. The full of waste water and 130 pounds when dimensions, minus the hoses, are empty. The waste water tank is on the right approximately 34.74 inches by 17.23 inches by side of the water recovery system 2 rack. The

30 PAYLOAD OVERVIEW NOVEMBER 2010

dimensions, minus the hoses, are can carry science experiments and serves as a approximately 32.54 inches by 17.30 inches by parking place for spare hardware that can be 18.77 inches. The unit is manufactured by replaced robotically once in space. For STS-133, Hamilton Sundstrand, Windsor Locks, Conn. Discovery will carry the ELC4 to the station to The WPA waste water tank is configured to be be positioned on the starboard 3 (S3) truss used in the Tranquility node to support lower inboard passive attachment system six crew members on the station. (PAS). ELC1 and ELC2 were placed on the station’s truss structure during STS-129. ELC1 Boeing is responsible for sustaining engineering is mounted on the port 3 (P3) truss element in the USOS. The hardware is sustained by the unpressurized cargo carrier attachment system Boeing ECLS and water evaluation team in (UCCAS) while ELC2 is placed on the S3 truss Houston. This team manages and maintains all upper outboard PAS. ECLS hardware and provides technical support to the station operations team in mission The weight of ELC4 is approximately control. 8,235 pounds. Remmele Engineering, based in Minneapolis, built the integral aluminum ELC EXPRESS LOGISTICS CARRIER 4 decks for NASA. Engineers from NASA Goddard Space Flight Center’s carriers The Express Logistics Carrier (ELC) is a development office developed the lightweight platform designed to support external payloads ELC design, which incorporates elements of mounted to the International Space Station both the express pallet and the unpressurized starboard and port trusses with either deep logistics carrier. Orbital Science Corporation space or Earthward views. Each pallet spans built the ELC. the entire width of the shuttle’s payload bay,

The International Space Station contains several unpressurized platforms that include ELCs 1-4 and External Storage Platforms (ESP) 1-2.

NOVEMBER 2010 PAYLOAD OVERVIEW 31

The ELC is designed to be carried in the space time while docked to the station, unshielded shuttle cargo bay to the station, fully integrated from incident radiation and orbital debris. with cargo. Four ELCs will be attached to the station before the scheduled retirement of the The following item will be carried on ELC4: space shuttle. Two ELCs will be attached to the Heat Rejection Subsystem Radiator S3 and two ELCs will be mated to the P3. By attaching at the S3/P3 sites, a variety of views The heat rejection subsystem (HRS) consists of such as deep space or Earthward directions a base, eight panels, torque panel, torque arm, with a combination of forward or aft pointing an interconnected fluid system, a scissors-type allows for many possible viewing deployment mechanism and a computer opportunities. Cargo stationed on the ELC will controlled motor/cable deployment system. be exposed to the microgravity and vacuum Part of the station’s external active thermal environments of space for extended periods of control system (EATCS), the HRS radiator rejects thermal energy via radiation.

32 PAYLOAD OVERVIEW NOVEMBER 2010

Radiator Specifications HRS radiators that are part of the EATCS (three each on S1 and P1). This spare HRS radiator Dimensions: Length: 74.6 feet will remain in a stowed configuration on ELC-4 Diameter: 11.2 feet until needed. Lockheed Martin manufactured Area: 1.554 ft.^2 the radiator. Boeing configured and integrated Weight: 2,475 pounds the HRS radiator onto the ELC4.

The EATCS provides heat rejection capabilities Boeing has the responsibility under its for pressurized modules and the main power Checkout, Assembly and Payload Processing distribution electronics on the starboard 0, Services contract with NASA for payload starboard 1 (S1) and port 1 (P1) trusses by a integration and processing for every major closed-loop, actively controlled, coolant loop to payload that flies on each space shuttle flight. maintain components at acceptable The Boeing PMM and ELC processing team temperatures. Heat is transferred to the HRS provides all engineering and hands-on work radiator via flowing liquid anhydrous including payload support, project planning, ammonia. Hot ammonia flows through the receipt of payloads, payload processing, radiator panels and heat is conducted from the maintenance of associated payload ground ammonia tubes to the cooler panel surface and systems and logistics support. This includes radiated to the “coldness” of deep space. integration of payloads into the space shuttle, Flowing ammonia exits the HRS radiator at a test and checkout of the payload with the cooler temperature so the closed-loop cycle orbiter systems, launch support and orbiter may continue. The HRS radiator unit post-landing payload activities. launching on ELC4 as part of the STS-133 mission is a spare, if needed, for one of the six

This graphic depicts the installed location of the PMM and ELC4 on the station.

NOVEMBER 2010 PAYLOAD OVERVIEW 33

ROBONAUT 2 or Mars. No funding was available to make R1 more than a prototype, however, and active Almost 200 people from 15 countries have work on the robot stopped in 2006. visited the International Space Station, but so far the orbiting complex has only ever had The same year, however, General Motors (GM) human crew members – until now. expressed an interest in hearing about the project. The company had been developing its Robonaut 2, the latest generation of the own dexterous robots and, after seeing what Robonaut astronaut helpers, is set to launch to NASA had already accomplished, proposed the space station aboard space shuttle teaming up. A Space Act Agreement was Discovery on the STS-133 mission. It will be the signed in 2007 to allow GM to benefit from first humanoid robot in space, and although its NASA’s experience and NASA to benefit from primary job for now is teaching engineers how GM’s funding. dexterous robots behave in space, the hope is that through upgrades and advancements, it In February 2010, R2 was unveiled – a faster, could one day venture outside the station to more dexterous, more technologically advanced help spacewalkers make repairs or additions to dexterous humanoid robot than had ever the station or perform scientific work. been seen before. Its potential was quickly recognized and space was made on one of the R2, as the robot is called, will launch inside the few remaining shuttle missions to provide it a Leonardo Permanent Multipurpose Module, ride to the space station. There, it will make which will be packed with supplies and both history as the first humanoid robot in equipment for the station and then installed space, and progress as engineers get their first permanently on the Unity node. Once R2 is look at how a humanoid robot actually unpacked – likely several months after it arrives performs in the absence of gravity. – it will initially be operated inside the Destiny laboratory for operational testing, but over Future time, both its territory and its applications R2’s first assignment will be aboard the could expand. There are no plans to return R2 International Space Station. The conditions to Earth. aboard the space station provide an ideal History proving ground for robots to work shoulder to shoulder with people in microgravity. Once Work on the first Robonaut began in 1997. The this has been demonstrated inside the station, idea was to build a humanoid robot that could software upgrades and lower bodies can be assist astronauts on tasks where another pair of added, allowing R2 to move around and hands would be helpful, or venture forth in eventually work outside in the vacuum of their stead for jobs either too dangerous for space. This will help NASA understand robotic crew members to risk or too mundane for them capabilities for future deep space missions. to spend time on. The result was R1, a human-like prototype of a robot that could As R2 technology matures, similar robots could perform maintenance tasks or be mounted on a be sent deeper into space to test the system in set of wheels to explore the surface of the moon more extreme thermal and radiation conditions.

34 PAYLOAD OVERVIEW NOVEMBER 2010

Someday, R2 could service communications, added to reduce electromagnetic interference weather and reconnaissance satellites, which and processors were upgraded to increase the have direct benefits on Earth. robot’s radiation tolerance. The original fans were replaced with quieter ones to The next step for robotic capabilities such as R2 accommodate the station’s restrictive noise would be to explore near-Earth objects, environment and the power system was including asteroids and comets, and eventually rewired to run on the station’s direct current Mars and Mars’ moons. The robot will serve as system, rather than the alternating current used a scout, providing advanced maps and soil on the ground. samples, and beginning work on the infrastructure that astronauts would need. The Space Readiness Testing crew that follows would then be much more prepared for the exploration ahead. Before being declared ready to brave the rigors of spaceflight, R2 was put through its paces to This evolution of capabilities for both robotic make sure the robot could both endure the and human exploration will make a planetary environment and exist in it without doing surface mission possible. This human-robotic damage. Tests were conducted to make sure partnership will allow surface missions to be the robot wasn’t too loud, didn’t emit conducted safely by a smaller crew – without electromagnetic waves that would interfere sacrificing mission plans and results. with other station systems and could run well on the station’s power system. It also There is a logical progression for the next underwent vibration testing that simulated the generation of space exploration. Our first look conditions it will experience during its launch at a new destination is through a telescope, then onboard space shuttle Discovery to make sure it through the eyes of a robotic precursor such as was ready for the ride. R2, followed by arrival of human explorers. Humans and robots exploring the solar system Working on the Station together will provide greater results than either could achieve alone, enabling an exciting future Initially, R2’s primary role on the space station of new discoveries. will be experimental. The robot will begin its life in space stationed in the Destiny laboratory, Upgrading for Space where it will be put through tasks and operations similar to ones that it has already R2 was designed as a prototype to be used here performed on Earth, which will allow engineers on Earth as a way to better understand what to work out the pitfalls of operating a dexterous would be needed to eventually send a robot to humanoid robot in space. As R2 proves its space. However, when R2 was unveiled, the mettle, the robot may graduate to station system was so impressive that mission maintenance tasks, such as vacuuming or managers decided to go ahead and send it to cleaning filters. And with upgrades that would the space station, but not without a few allow it to function in the vacuum of space, it upgrades. Outer skin materials were could also perform repairs on the outside of the exchanged to meet the station’s stringent station or simply help astronauts as work flammability requirements; shielding was outside.

NOVEMBER 2010 PAYLOAD OVERVIEW 35

Specifications

Materials: Nickel-plated carbon fiber and aluminum Weight: 300 pounds Height: 3 feet, 3.7 inches (from waist to head) Shoulder width: 2 feet, 7.4 inches Degrees of freedom: 42 Sensors: 350+ Processors: 38 Power PC Processors Energy usage: 120 volts DC

What Robonauts are Made Of

A robot meant to work with humans and use human tools begins to look humanlike by default. However R2’s head Behind R2’s visor are four visible light houses not its brain, but its vision equipment. cameras – two to provide stereo vision for the robot and its operators and two auxiliary cameras.

A fifth infrared camera is R2 has three degrees housed in the mouth area for of freedom in its depth perception. neck, allowing it to look left, right, up or down.

Each arm boasts Each arm is seven degrees of 2 feet, freedom and the strength to hold 8 inches long, 20 pounds in any pose in Earth’s gravity. giving the R2 a total wingspan of Here on Earth and at the space 8 feet. station, R2’s backpack holds its power conversion system, allowing it to basically be plugged in. On another planetary surface the backpack would hold the robot’s batteries.

Robonaut 2’s hands have 12 degrees of freedom -- four in the thumb, three each in the index and middle R2 thinks with its stomach – literally. fingers and one each in the ring and pinky fingers. Each With its head full of cameras, the only finger has a grasping force of 5 pounds. place with enough room for a brain is the robot’s torso.

36 PAYLOAD OVERVIEW NOVEMBER 2010

RENDEZVOUS & DOCKING

Discovery’s launch for the STS-133 mission is will document the thermal protection system precisely timed to lead to a link up with the armed with a camera outfitted with a 400 mm International Space Station about 220 miles lens providing three-inch resolution. above the earth. A series of engine firings during the first two days of the mission will The photography is one of several techniques bring the shuttle to a point about 50,000 feet used to inspect the shuttle’s outer surface for behind the station. Once there, Discovery will possible damage. Areas of special interest start its final approach. About 2.5 hours before include the thermal protection tiles, the docking, the shuttle’s jets will be fired during reinforced carbon-carbon panels along the wing what is called the terminal initiation burn. The leading edges and the nosecap, landing gear shuttle will cover the final distance to the doors and the elevon cove. The digital photos station during the next orbit. will be downlinked through the station’s Ku-band communications system for analysis As Discovery moves closer, its rendezvous by imagery experts in mission control. radar system and trajectory control sensor will provide the crew with range and closing-rate When Discovery completes its back flip, it will data. Several small correction burns will place be back where it started with its payload bay the shuttle about 1,000 feet below the station. facing the station. Lindsey then will fly the shuttle through a quarter circle to a position Commander Steve Lindsey, with help from about 400 feet directly in front of the station. Pilot Eric Boe and other crew members, will From that point, he will begin the final manually fly the shuttle for the remainder of approach to docking to the Pressurized Mating the approach and docking. Adapter 2 at the forward end of the Harmony node. Lindsey will stop Discovery about 600 feet below the station. Timing the next steps to The shuttle crew members will operate laptop occur with proper lighting, he will maneuver computers that process the navigational data, the shuttle through an approximate eight- the laser range systems and Discovery’ docking minute back flip called the Rendezvous Pitch mechanism. Maneuver, also known as the R-bar Pitch Maneuver since Discovery is in line with an Using a video camera mounted in the center of imaginary vertical R-bar directly below the the orbiter docking system, Lindsey will line up station. During this maneuver, station crew the docking ports of the two spacecraft. If members Fyodor Yurchikhin and Shannon necessary, he will pause the shuttle 30 feet from Walker will photograph Discovery’s upper and the station to ensure the proper alignment of lower surfaces through windows of the Zvezda the docking mechanisms. He will maintain the Service Module. Yurchikhin will use a digital shuttle’s speed relative to the station at about camera equipped with an 800 mm lens to one-tenth of a foot per second, while both provide up to one-inch resolution and Walker Discovery and the station are moving at about

NOVEMBER 2010 RENDEZVOUS & DOCKING 37

17,500 mph. Lindsey will keep the docking Once the shuttle is about two feet from the mechanisms aligned to a tolerance of three station and the docking devices are clear of one inches. another, Boe will turn the steering jets back on and manually control Discovery within a tight When Discovery makes contact with the corridor as the shuttle separates from the station, preliminary latches will automatically station. link the two spacecraft. The shuttle’s steering jets will be deactivated to reduce the forces Discovery will move to a distance of about acting at the docking interface. Shock absorber 450 feet, where Boe will begin to fly around the springs in the docking mechanism will dampen station. Discovery will circle the shuttle around any relative motion between the shuttle and the station at a distance of 600-700 feet. station. Once the shuttle completes 1.5 revolutions of Once motion between the shuttle and the the complex, Boe will fire Discovery’s jets to station has been stopped, the docking ring will leave the area. The shuttle will begin to be retracted to close a final set of latches increase its distance behind the station with between the two vehicles. each trip around the earth while the crew conducts one last inspection of the heat shield UNDOCKING, SEPARATION AND using the Orbiter Boom Sensor System. DEPARTURE The distance will be close enough to allow the At undocking time, the hooks and latches will shuttle to return to the station in the unlikely be opened and springs will push the shuttle event that the heat shield is damaged, away from the station. Discovery’s steering jets preventing the shuttle’s safe re-entry. will be shut off to avoid any inadvertent firings during the initial separation.

38 RENDEZVOUS & DOCKING NOVEMBER 2010

SPACEWALKS

Astronaut Tim Kopra is pictured during the first of five spacewalks on the International Space Station by the STS-127 crew. Kopra, who was joined by astronaut Dave Wolf on this spacewalk, holds onto a handrail on the Harmony node.

Following the failure of a pump module on the Kopra, the lead spacewalker for the mission, International Space Station in August, the will wear a spacesuit marked with solid red spacewalk plan for STS-133 underwent a major stripes, while Drew will wear an all-white overhaul. What had been planned for spacesuit. These will be the second and third noncritical tasks that simply had not yet found spacewalks for Kopra, who performed one a home became a chance to finish up work spacewalk lasting 5 hours and 2 minutes during started on the three unplanned spacewalks the STS-127 mission in July of 2009. It will be conducted by Expedition 24 Flight Engineers Drew’s first time to venture outside the space Tracy Caldwell Dyson and Doug Wheelock. station.

For the STS-133 mission, Mission Specialists When a spacewalk – also called extravehicular Tim Kopra and Al Drew will spend 13 hours activity (EVA) for short – is being conducted, outside the station on flight days 5 and 7. one crew member inside the International

NOVEMBER 2010 SPACEWALKS 39

Space Station is assigned the job of is lowered again. Approximately 50 minutes Intravehicular (IV) officer, or spacewalk after the spacewalkers don their spacesuits, the choreographer. In this case, that crew member prebreathe protocol will be complete. will be Mission Specialist Nicole Stott. The The procedure enables spacewalks to begin spacewalks will also require astronauts inside earlier in the crew’s day than was possible the station to be at the controls of the station’s before the protocol was adopted. 58-foot-long robotic arm to maneuver an ammonia tank assembly and other pieces of EVA-1 hardware. Mission Specialist Michael Barratt and Expedition 25 Flight Engineer Duration: 6 hours, 30 minutes Shannon Walker will be given that EVA Crew: Kopra and Drew responsibility for this mission. During the first IV Crew: Stott spacewalk, they will be ferrying Kopra between Robotic Arm Operators: Barratt and Walker worksites as he carries the failed pump module EVA Operations: to a storage position. During the second spacewalk, Kopra will ride on the arm as he • J612 extension cable installation stows a lightweight adaptor plate assembly in • Install pump module vent tool Discovery’s cargo bay, installs a video camera on Dextre, the special purpose dexterous • Failed pump module storage manipulator, and removes some of Dextre’s • Relocate a tool stanchion insulation. • Install camera wedge on starboard 1 truss Preparations will start the night before each segment spacewalk, when the astronauts spend time in • the station’s Quest airlock. This practice is Install extensions to the mobile transporter called the campout prebreathe protocol and is rail used to purge nitrogen from the spacewalkers’ • Expose Message in a Bottle experiment to systems and prevent decompression sickness, space also known as “the bends.” Of course, one of the primary goals of STS-133 During the campout, Kopra and Drew will is to deliver the new Permanent Multipurpose isolate themselves inside the airlock while the Module (PMM), to the space station. But before air pressure is lowered to 10.2 pounds per it can be attached to the Unity node, an square inch (psi). The station is kept at the extension cable must be installed on the J612 near-sea-level pressure of 14.7 psi. The cable. The cable, which powers secondary morning of the spacewalk, the astronauts will airlock heaters, will be inaccessible after the wear oxygen masks while the airlock’s pressure PMM is installed in its current state. The is raised back to 14.7 psi for an hour and the extension cable will make any future hatch between the airlock and the rest of the replacements of the system that might be station is opened. That allows the spacewalkers necessary easier. to perform their morning routines before returning to the airlock, where the air pressure Installing the extension cable will take Kopra and Drew about 30 minutes. To do so, Kopra

40 SPACEWALKS NOVEMBER 2010 will remove dust caps from the cable and he will fold back two flaps of insulation on a release some wire ties currently holding the remote power control module, relocate a tool J612 cable in place. Then, he will disconnect the stanchion and retrieve another foot restraint, original cable from the Unity node and connect this one to store inside the airlock. the extension cable in its place, before tying Afterward, Kopra and Drew will come back down the extension cable. Drew, meanwhile, together to install a camera wedge on a video will connect the extension cable to the original camera on the first starboard segment of the cable, which runs to the Quest airlock. He will station’s truss. The wedge will give the camera also work to secure the cables in place. added clearance that it will need once the From there, Kopra will move to the external ExPRESS Logistics Carrier 4 that Discovery stowage platform 2, where a foot restraint will delivered is installed nearby. be waiting for him to attach it to the space To install the wedge, Drew will remove the station’s robotic arm. On it, Kopra will move to camera’s stanchion by removing one bolt. The the payload orbital replacement unit wedge will be secured to the truss using a bolt, accommodation (POA), which is basically one and then the stanchion bolted back onto the of the robotic arm “hands” without the arm, wedge. The task should take about an hour. used to temporarily store equipment. In this case, the equipment is the pump module that The spacewalkers will then move together failed over the summer. To remove the pump further down the starboard truss to the solar module from the POA, Kopra will install a alpha rotary joint at the starboard three handle on the module and then have the segment. There, they will be installing two robotics officers release the POA’s hold on the extensions to the station’s mobile transporter it. He will carry the module back to the track, which will allow the mobile transporter external stowage platform, which will be its to travel the entire length of the track with the long-term storage location. CETA cart and still reach all the worksites. Each extension (one on either rail of the track) While Kopra retrieves the module, Drew will will be secured by two bolts. retrieve from the port truss’ crew equipment and translation aid, (CETA), cart a tool that will Drew and Kopra will wrap up their work at S3 be used to remove remaining ammonia from by pushing two “stops” out of the way on the the pump module. rails – one meant to keep the mobile transporter from passing and one meant to keep a Kopra and Drew will work together to secure spacewalker’s tether from passing. the pump module. Four bolts will be installed to hold it in place. They will also install the tool The last task for the first spacewalk of the Drew retrieved – called the vent tool – for use mission will be for Kopra and Drew to on the second spacewalk. participate in the Japan Aerospace Exploration Agency activity called Message in a Bottle. Once that task is over, Kopra will climb off of They will open and fill a metal cylinder that has the robotic arm. While he does so, Drew will been signed by other astronauts who have move to a piece of the station’s truss near the flown in space. The bottle will then be returned center of the system – the Z1 segment – where to the ground for public display.

NOVEMBER 2010 SPACEWALKS 41

Astronaut Alvin Drew dons a training version of his spacesuit in preparation for a spacewalk training session in the waters of the Neutral Buoyancy Laboratory near NASA’s Johnson Space Center. Crewmate Nicole Stott assists Drew.

EVA-2 • Install Dextre camera

Duration: 6 hours, 30 minutes • Remove Dextre insulation cover EVA Crew: Kopra and Drew • Install light in port crew and equipment IV Crew: Stott translation aid cart Robotic Arm Operators: Barratt and Walker • Reconfigure port radiator beam valve EVA Operations: module insulation • Vent remaining ammonia from failed pump • Troubleshoot port radiator grapple fixture module stowage beams • Stow lightweight adapter plate assembly in • Remove insulation on Tranquility node Discovery’s cargo bay power cables • Remove insulation on the ExPRESS logistics • Install covers on Dextre, space station carrier avionics robotic arm and payload orbital replacement unit attachment cameras

42 SPACEWALKS NOVEMBER 0201

The second spacewalk of the mission will The spacewalkers will continue to work include one more task to finish up the work separately throughout the rest of the with the failed pump module. That task – spacewalk. The robotic arm will fly Kopra to removing the remaining ammonia from the the special purpose dexterous manipulator, or pump module – will take Drew about an hour. Dextre. There, he will install a second camera The balance of the two spacewalker’s six and a (using one bolt) on the robot and remove an half hours scheduled outside the station will be unnecessary insulation blanket, while Drew spent on the assorted tasks originally assigned installs a light on the port CETA cart. To install to the STS-133 mission. the light, Drew will disconnect a cable on a stanchion on the CETA cart and connect it to The pump module work will be first up on the new light, then drive one bolt to hold it in Drew’s timeline. As the vent tool will have place. been installed on the first spacewalk, Drew will simply have to open the vent and wait about From there, Drew will travel to a radiator beam two minutes for ammonia to be vented out to on the first port segment of the truss and install space. (The tool allows it to vent without insulation on its valve module fluid line. He contaminating Drew’s spacesuit with will also spend some time troubleshooting a ammonia.) Once it is done, he will remove the radiator grapple fixture stowage beam. The tool and take it back to the Quest airlock. beam, which was originally installed on STS-131, would be used temporarily to store Meanwhile, Kopra will be climbing back into handles that would be necessary if a radiator the foot restraint on the station’s robotic arm. ever needed to be replaced. However, during He will ride the robotic arm to the end of that its installation, the astronauts noticed the beam module to pick up a lightweight adapter plate was looser than they expected. Experts on the assembly, which has been used to attach ground think this might be because the two experiments to the exterior of Columbus. bolts securing it did not seat properly or were Kopra will store it on the sidewall carrier in the misaligned. shuttle’s cargo bay to return home with Discovery. This task was originally scheduled So, to fix that, Drew will be releasing the two for STS-131, but canceled due to time bolts and redriving them. If that does not work, constraints. Kopra will need to remove one bolt Drew may be asked to remove the beam to retrieve the plate and install one bolt to altogether and check it for clearance issues or secure it in the cargo bay. Drew will assist, if even bring it inside for further troubleshooting. needed. Kopra may assist Drew, if necessary.

When he is not assisting Kopra with the Afterward, Drew will move to the Tranquility adapter plate, Drew will remove some node to remove some insulation covering insulation from the avionics assembly on the electrical connectors. In the meantime, Kopra new ExPRESS Logistics Carrier 4 and retrieve will have gotten off the robotic arm. Since he’ll three sets of stowage bags from the CETA cart be in the vicinity, his next task will be to install on the port side of the station’s truss system. a lens cover on the camera on the arm’s elbow joint. The cover will protect the lens from any erosion that might be caused by the thruster

NOVEMBER 2010 SPACEWALKS 43

plume of visiting vehicles that the arm is used Kopra will install one of Dextre’s cameras to dock. It is attached using a lever that locks it (the one he did not install earlier in the into place. spacewalk). And Drew’s last tasks will be to install a lens cover on the POA’s camera. The rest of the spacewalk will be spent installing similar covers on other cameras.

44 SPACEWALKS NOVEMBER 2010

EXPERIMENTS

The STS-133 mission will deliver the Permanent urine monitoring system, which will simplify Multipurpose Module, a veteran pressurized for crew members the process of collecting cargo carrier that has been converted to a waste samples while in the station’s waste and permanent storage and research module. hygiene compartment. Inside the Italian-built Leonardo module will be the first human-like robot to be tested in orbital The STS-133 mission includes a mix of research conditions, and a host of experiments and that will be performed on the space shuttle supplies for the International Space Station Discovery and on the station during and after crew. the shuttle mission. Among the new experiments being delivered by Discovery will Nearly 150 experiments are continuing aboard be the Microheater Array Boiling Experiment the station as the transition from assembly and the Nucleate Pool Boiling Experiment, both work to expanded research on the international of which will use the new BXF facility, and a laboratory progresses. They span the basic cucumber-development experiment called categories of biological and biotechnology, Dynamism of Auxin Efflux Facilitators human research, physical and materials Responsible for Gravity-regulated Growth and sciences, technology development, Earth and Development in Cucumber (CsPINs), which space science and educational activities. will continue to expand the body of knowledge on how plants react to the microgravity Robonaut 2 (R2), will be installed in the environment. U.S. Destiny laboratory, providing scientists and engineers on the ground and crews on the Research activities on the shuttle and station are station an opportunity to test how humans and integrated to maximize return during station human-like robots can work shoulder-to- assembly. The shuttle serves as a platform for shoulder in microgravity. Once this has been completing short-duration research, while demonstrated inside the station, software providing supplies and sample-return for upgrades and lower bodies can be added, ongoing research on station. potentially allowing R2 to move around inside the station and eventually work outside in the SHORT-DURATION EXPERIMENTS TO vacuum of space. This will help NASA BE PERFORMED ON STS-133 understand robotic capabilities for future deep space missions. Biology and Biotechnology

Three new facilities will be delivered to the Mouse Immunology-2 will expand the station for use in a variety of investigations: the knowledge base of the effects of space Boiling Experiment Facility (BXF), which will environment on mammalian immunology and support microgravity experiments on the heat provide fundamental knowledge for current transfer and vapor removal processes in applications that form a foundation for future boiling; the eighth Express rack, which will be long-duration space exploration missions. installed in the Destiny laboratory, and the

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Principal investigator: Paula Dumars, Ames Surveillance Site in Hawaii when the space Research Center, Moffett Field, Calif. (NASA) shuttle fires its engines at night or twilight. A telescope and all-sky imagers will take images National Lab Pathfinder – Vaccine and data while the space shuttle flies over the (NLP-Vaccine) is a pathfinder investigation for Maui site. The images are analyzed to better the use of the International Space Station as a understand the interaction between the National Laboratory after station assembly is spacecraft plume and the upper atmosphere of complete. It contains several different Earth. Principal investigator: Rainer A. pathogenic (disease causing) organisms. This Dressler, Hanscom Air Force Base, Lexington, research is investigating the use of space flight Mass. (NASA) to develop potential vaccines for the prevention of different infections caused by these Ram Burn Observations (RAMBO) an pathogens on Earth and in microgravity. experiment uses a satellite to observe space (NASA) shuttle orbital maneuvering system engine burns. Its purpose is to improve plume Growth and Survival of Colored Fungi in models, which predict the direction the plume, Space (CFS-A) is an experiment designed to or rising column of exhaust, will move as the determine the effect of microgravity and cosmic shuttle maneuvers in space. Understanding the radiation on the growth and survival of colored direction in which the spacecraft engine plume, fungi species. Principal investigators: Dumitru or exhaust flows could be significant to the safe Hasegan, George Mogildea, Marian Mogildea arrival and departure of spacecraft on current Romanian Institute for Space Science, and future exploration missions. Principal Bucharest. (ESA) investigator: William L. Dimpfl, Aerospace Human Research Corporation, Los Angeles. (NASA)

Sleep-Wake Actigraphy and Light Exposure Shuttle Exhaust Ion Turbulence Experiments During Spaceflight-Short (Sleep-Short) (SEITE), a Department of Defense experiment, examines the effects of space flight on the uses space-based sensors to detect the sleep cycles of the astronauts during space ionospheric turbulence inferred from the radar shuttle missions. Advancing state-of-the-art observations from previous space shuttle technology for monitoring, diagnosing and orbital maneuvering system burn experiments assessing treatment of sleep patterns is vital to using ground-based radar. Principal treating insomnia on Earth and in space. investigator: Paul A. Bernhardt, Naval Charles A. Czeisler, Brigham and Women’s Research Laboratory, Washington D.C. (NASA) Hospital, Harvard Medical School, Boston, Shuttle Ionospheric Modification with Pulsed Mass. (NASA) Localized Exhaust Experiments (SIMPLEX), a Technology Department of Defense experiment, investigates plasma turbulence driven by rocket Maui Analysis of Upper Atmospheric exhaust in the ionosphere using ground-based Injections (MAUI), a Department of Defense radars. Principal investigator: Paul A. experiment, observes the space shuttle engine Bernhardt, Naval Research Lab, Washington exhaust plumes from the Maui Space D.C. (NASA)

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RESEARCH SAMPLES/HARDWARE TO the station speak directly with large groups of BE DELIVERED TO STATION ON the general public, showing teachers, students, DISCOVERY parents, and communities how amateur radio energizes students about learning. ISS Ham Biology and Biotechnology Radio inspires students about science, technology engineering and mathematics by Biomedical Analyses of Human Hair Exposed allowing them to talk directly with the crews to a Long-term Space Flight (Hair) examines living and working aboard the station. the effect of long-duration spaceflight on gene Principal investigator: Kenneth Ransom, expression and trace element metabolism in the Johnson Space Center, Houston. (NASA) human body. Principal investigator: Chiaki Mukai, JAXA, Tsukuba, Japan. (JAXA) Japan Aerospace Exploration Agency Education Payload Observation 6 (JAXA Dynamism of Auxin Efflux Facilitators EPO 6) activities demonstrate artistic activities Responsible for Gravity-regulated Growth in the space station’s Kibo laboratory to and Development in Cucumber (CsPINs) uses enlighten the general public about microgravity cucumber seedlings to analyze the effect of research and human space flight. Principal gravity on the expressions of Auxin Efflux investigators: Takuro Osaka, University of Facilitators, or CsPINs, and unravel their Tsukuba, Tsukuba, Japan; Teruhiko Tabuchi, contributions to gravimorphogenesis (peg JAXA, Tsukuba, Japan; Yoshie Ozeki, JAXA, formation). The experiment also differentiates Tsukuba, Japan. (JAXA) hydrotropism from gravitropism in roots and compares the expression of CsPINs to figure Human Research out the interacting mechanism between the two Bisphosphonates as a Countermeasure to tropisms. Principal investigator: Hideyuki Space Flight Induced Bone Loss Takahashi, Tohoku University, Sendai, Miyagi, (Bisphosphonates) will determine whether Japan. (JAXA) antiresorptive agents, which help reduce bone Mycological Evaluation of Crew Exposure to loss, in conjunction with the routine inflight ISS Ambient Air 3 (Myco-3) evaluates crew exercise program, will protect station crew exposure to microorganisms such as fungi that members from the regional decreases in bone can act as allergens via inhalation and adhesion mineral density documented on previous to the skin from space station ambient air. station missions. Adrian LeBlanc, Division of Principal investigator: Chiaki Mukai, JAXA, Space Life Sciences, Universities Space Tsukuba, Japan. (JAXA) Research Association, Houston, and Toshio Matsumoto, University of Tokushima, Educational Activities Kuramoto, Japan. (NASA)

International Space Station Ham Radio Elaboratore Immagini Televisive – Space 2 (ISS Ham Radio) allows crewmembers on the (ELITE-S2) will investigate the connection station to perform ham radio contacts. With the between brain, visualization and motion in the help of amateur radio clubs and ham radio absence of gravity. By recording and analyzing operators, astronauts and cosmonauts aboard the three-dimensional motion of astronauts, this

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study will help engineers apply ergonomics pharmaceuticals, on nutritional status and into future spacecraft designs and determine nutrient requirements for astronauts. Principal the effects of weightlessness on breathing investigator: Scott M. Smith, Johnson Space mechanisms for long-duration missions. This Center, Houston. (NASA) experiment is a cooperative effort with the Italian Space Agency, ASI. Principal Dietary Intake Can Predict and Protect investigator: Francesco Lacquaniti, M.D., Against Changes in Bone Metabolism during University of Rome Tor Vergata, Rome, Italy. Spaceflight and Recovery (Pro K) is NASA’s (NASA) first evaluation of a dietary countermeasure to decrease bone loss of astronauts. Pro K Cardiac Atrophy and Diastolic Dysfunction proposes that a flight diet with a decreased During and After Long Duration Spaceflight: ratio of animal protein to potassium will lead to Functional Consequences for Orthostatic decreased loss of bone mineral. Pro K will have Intolerance, Exercise Capability and Risk for an impact on the definition of nutritional Cardiac Arrhythmias (Integrated requirements and development of food systems Cardiovascular) will quantify the extent, time for future exploration missions, and could yield course and clinical significance of cardiac a method of counteracting bone loss that would atrophy, or decrease in the size of the heart have virtually no risk of side effects. Principal muscle, associated with long-duration space investigator: Scott M. Smith, Johnson Space flight. This experiment will also identify the Center, Houston. (NASA) mechanisms of this atrophy and the functional consequences for crew members who will National Aeronautics and Space spend extended periods of time in space. Administration Biological Specimen Principal investigators: Benjamin D. Levine, Repository (Repository) is a storage bank that Institute for Exercise and Environmental is used to maintain biological specimens over Medicine, Presbyterian Hospital and University extended periods of time and under of Texas Southwestern Medical Center at well-controlled conditions. Biological samples Dallas, Michael W. Bungo, University of Texas from the space station, including blood and Medical School, Houston. (NASA) urine, are collected, processed and archived during the preflight, in-flight and post-flight Nutritional Status Assessment (Nutrition) is phases of space station missions. This the most comprehensive in-flight study done by investigation has been developed to archive NASA to date of human physiologic changes biosamples for use as a resource for future during long-duration space flight. This study space flight-related research. Curator: includes measures of bone metabolism, Kathleen A. McMonigal, Johnson Space Center, oxidative damage, nutritional assessments and Houston. (NASA) hormonal changes. This study will affect both the definition of nutritional requirements and Evaluation of Maximal Oxygen Uptake and development of food systems for future space Submaximal Estimates of VO2max Before, exploration missions. This experiment will During, and After Long Duration also help to understand the impact of International Space Station Missions countermeasures, such as exercise and (VO2max) documents changes in maximum oxygen uptake for crew members on board the

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station on long-duration missions. Accurate Rhythms) examines the effect of long-term VO2max measurements will allow NASA to microgravity exposure on cardiac determine if submaximal exercise testing data autonomic function by analyzing 24-hour will provide results that allow accurate electrocardiogram of long-duration station crew estimation of the crew members’ aerobic members. Principal investigator: Chiaki capacity during and after space flight. Data Mukai, JAXA, Tsukuba, Japan. (JAXA) from this experiment will help refine future test requirements and optimize the testing used to Physical and Materials Sciences track aerobic capacity during and after space Burning and Suppression of Solids (BASS) flight. Principal investigator: Alan D. Moore, will test the hypothesis that materials in Jr., Johnson Space Center, Houston. (NASA) microgravity burn as well as, if not better than, Cardiovascular Health Consequences of the same material in normal gravity with Long-Duration Space Flight (Vascular) studies other conditions being identical (i.e., the impact of space flight on the blood vessels pressure, oxygen concentration, temperature). of long-duration space explorers. Data is Paul Ferkul, National Center for Space collected before, during and after space flight to Exploration Research, Cleveland. (NASA) assess inflammation of the artery walls, changes Binary Colloidal Alloy Test – 6 (BCAT-6) is a in blood vessel properties and cardiovascular suite of investigations that photograph fitness to create specific countermeasures for randomized colloidal samples in microgravity future long-duration space explorers beyond to determine their resulting structure over time. low Earth orbit. Principal investigator: Richard The use of EarthKAM software and hardware Lee Hughson, University of Waterloo, will allow the scientists to capture the kinetics, Waterloo, Ontario, Canada. (CSA) or evolution, of their samples, as well as the Mental Representation of Spatial Cues During final equilibrium state of each sample. Results Space Flight (3D-Space) investigates the effects will help scientists develop fundamental of exposure to microgravity on the mental physics concepts previously hindered by the representation of spatial cues by astronauts effects of gravity. Data may lead to during and after spaceflight. The absence of the improvements in supercritical fluids used in gravitational frame of reference during space rocket propellants biotechnology applications, flight could be responsible for disturbances in and advancements in fiber-optics technology. the mental representation of spatial cues, such Principal investigators: David A. Weitz and as the perception of horizontal and vertical Peter J. Lu, Ph.D., Harvard University, lines, the perception of an object’s depth and Cambridge, Mass.; Paul M. Chaikin, Princeton the perception of a target’s distance. Principal University, Princeton, N.J., Arjun Yodh, investigator: Gilles Clement, Centre National University of Pennsylvania, University Park, de la Recherche Scientifique, Toulouse, France. Pa.; Barbara Frisken, Ph.D., Simon Fraser (ESA) University, Burnaby, British Columbia, Canada; Matthew Lynch, Ph.D., Procter and Gamble, Effect of Long-term Microgravity Exposure Cincinnati, Ohio. (NASA) on Cardiac Autonomic Function by Analyzing 24-hours Electrocardiogram (Biological

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Structure and Liftoff In Combustion Dhir, University of California – Los Angeles. Experiment (SLICE) investigates the structure (NASA) of lifting and lifted flames; whereby the flame detaches from the nozzle and stabilizes at a Robonaut 2 will provide an ideal proving downstream position. Results from this ground for robots to work shoulder-to-shoulder investigation are used to maximize the science with people in microgravity. Once this has return from the future Coflow Laminar been demonstrated inside the station, software Diffusion Flame experiment. Principal upgrades and lower bodies can be added, investigator: Marshall B. Long, Yale University, allowing R2 to move around and eventually New Haven, Conn. (NASA) work outside in the vacuum of space. This will help NASA understand robotic capabilities for Production of High Performance future deep space missions. Principal Nanomaterials in Microgravity 2 investigator: Myron A. Diftler, Johnson Space (Nanoskeleton-2) aims to clarify the effect of Center, Houston. (NASA) gravity on oil flotation, sedimentation and convection on crystals generated in Vehicle Cabin Atmosphere Monitor (VCAM) microgravity. Principal investigators: identifies gases that are present in minute Masakazu Abe, Tokyo University of Science; quantities in the International Space Station Naokiyo Koshikawa, JAXA. (JAXA) breathing air that could harm the crew’s health. If successful, instruments like VCAM could Technology accompany crew members during long- duration exploration missions. Principal Boiling eXperiment Facility – Microheater investigator: Ara Chutjian, Ph.D., California Array Boiling Experiment (BXF-MABE) will Institute of Technology and Jet Propulsion obtain data to understand the process involved Laboratory, Pasadena, Calif. (NASA) with boiling in gravity and microgravity. The research should enable the development of Passive Dosimeter for Lifescience Experiment more efficient cooling systems on future in Space (PADLES) measures radiation spacecraft and on Earth. Principal investigator: exposure levels onboard the station using Jungho Kim, Ph.D., University of Maryland, passive and integrating dosimeters to detect College Park, Md. (NASA) radiation levels. Principal investigator: Aiko Nagamatsu, Japan Aerospace Exploration Boiling Experiment Facility – Nucleate Pool Agency, Tsukuba, Japan. (JAXA) Boiling Experiment (BXF-NPBX) will provide an understanding of heat transfer and vapor Facilities removal processes that take place during nucleate boiling from a well characterized Expedite the Processing of Experiments to surface in microgravity. Such an Space Station Rack 8 (EXPRESS Rack 8) is a understanding is needed for optimum design multipurpose payload rack system that stores and safe operation of heat exchange equipment and supports experiments aboard the space employing phase change for transfer of heat in station. The EXPRESS Rack system supports microgravity. Principal investigator: Vijay science experiments in any discipline by providing structural interfaces, power, data,

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cooling, water and other items needed to Physiology and Biochemistry, Faculty of operate science experiments in space. Principal Forestry and Environmental Management, investigator: Annette Sledd, Marshall Space University of New Brunswick, Fredericton, Flight Center, Huntsville, Ala. (NASA) N.B., Canada. (CSA)

Urine Monitoring System (UMS) is designed Gravity Related Genes in Arabidopsis – A to collect an individual crew member’s urine (Genara-A) seeks to provide an understanding void, gently separate liquid from air, accurately of microgravity induced altered molecular measure each void volume, allow for void activities which will help to find plant systems sample acquisition, and discharge the that compensate the negative impact on plant remaining urine into the waste and hygiene growth in space. Principal investigator: compartment onboard the International Space Eugenie Carnero-Diaz, Universite Pierre et Station. Principal investigator: Daniel L. Marie Curie, Paris. (ESA) Feeback, Johnson Space Center, Houston. (NASA) Regulation by Gravity of Ferulate Formation in Cell Walls of Rice Seedlings (Ferulate) tests RESEARCH SAMPLES/HARDWARE TO the hypothesis that microgravity modifies BE RETURNED ON DISCOVERY ferulic acid thereby decreasing the mechanical strength of cell walls. Principal investigator: Biology and Biotechnology Kazuyuki Wakabayashi, Osaka City University, Osaka, Japan. (JAXA) National Laboratory Pathfinder – Cells – 4: Jatropha-2 (NLP-Cells-4) assesses the effects of Biomedical Analyses of Human Hair Exposed microgravity on the formation, establishment to a Long-term Space Flight (Hair) examines and multiplication of undifferentiated cells and the effect of long-duration space flight on gene evaluates changes in cell structure, growth and expression and trace element metabolism in the development, genetic changes and differential human body. Principal investigator: gene expression of Jatropha curcas, a biofuel Chiaki Mukai, JAXA, Tsukuba, Japan. (JAXA) plant. This study identifies significant changes that occur in microgravity which could Hydrotropism and Auxin-Inducible Gene contribute to the development of new cultivars expression in Roots Grown Under of this biofuel plant. Principal investigator: Microgravity Conditions (HydroTropi) Wagner Vendrame, University of Florida, determines whether hydrotropic response can Homestead, Fla. (NASA) be used for the control of cucumber, Cucumis sativus root growth orientation in microgravity. Cambium (Cambium) is one in a pair of Principal investigator: Hideyuki Takahashi, investigations which uses the advanced Tohoku University, Sendai, Japan. (JAXA) biological research system. Cambium seeks definitive evidence that gravity has a direct Microbial Dynamics in International Space effect on cambial cells, which are cells located Station – II (Microbe-II) monitors microbes in under the inner bark where secondary growth the Kibo laboratory which may affect the health occurs, in willow Salix babylonica. Principal of crew members. The monitoring of the stress investigator: Rodney Savidge, Professor of Tree from microbes to a crew member is evaluated

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as a space medical impact. Principal Microgravity leads to an activation of sodium investigators: Koichi Makimura, Teikyo retaining hormones even at normal sodium University; Masao Nasu, Osaka University. intake levels and causes positive sodium (JAXA) balances. SOLO is a continuation of extensive research into the mechanisms of fluid and salt Mycological Evaluation of Crew Exposure to retention in the body during bed rest and space ISS Ambient Air (Myco) evaluates crew flights. Principal investigator: Martina Heer, exposure to microorganisms such as fungi that Institute of Aerospace Medicine, Cologne, can act as allergens via inhalation and adhesion Germany. (ESA) to the skin from space station ambient air. Principal investigator: Chiaki Mukai, JAXA, Educational Activities Tsukuba, Japan. (JAXA) NanoRacks-CubeLabs is a multipurpose Human Research research facility aboard the International Space Station which supports NanoRacks-CubeLabs Validation of Procedures for Monitoring Crew modules by providing power and data transfer Member Immune Function (Integrated capabilities to operate investigations in Immune) will assess the clinical risks resulting microgravity. (NASA) from the adverse effects of space flight on the human immune system and will validate a Message in a Bottle, Education Payload flight-compatible immune monitoring strategy. Operations 5 (JAXA EPO 5) includes Researchers will collect and analyze blood, curriculum-based educational activities that urine and saliva samples from crew members will demonstrate basic principles of science, before, during and after space flight to monitor mathematics, technology, engineering and changes in the immune system. Changes in the geography. These activities are videotaped and immune system will be monitored by collecting then used in classroom lectures. EPO is and analyzing blood and saliva samples from designed to support the NASA mission to crew members during flight and blood, urine inspire the next generation of explorers. and saliva samples before and after space flight. Message in a Bottle involves an astronaut on a Principal investigator: Clarence Sams, Johnson spacewalk capturing space in a bottle that will Space Center, Houston. (NASA) be brought back to Earth. In doing so, the astronaut would not only create a memento of Long Term Microgravity: A Model for his or her time in space but also a message for Investigating Mechanisms of Heart Disease present and future humankind. Once the bottle with New Portable Equipment (Card) studies is placed in people’s hands, it would become a blood pressure decreases in the human body conduit between humans and space, between exposed to microgravity onboard the station. this world and the one beyond us. It would Principal investigator: Peter Norsk, University inspire wonder about our extraterrestrial of Copenhagen, Copenhagen, Denmark. (ESA) activities in this new age of exploration and SOdium LOading in Microgravity (SOLO) make us realize that Earth itself is merely one studies the mechanisms of fluid and salt small part of the entire universe. Principal retention in the body during space flight. investigators: Shiro Matsui, Kyoto City

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University of Arts, Kyoto, Japan; Hidekazu Mecanique des Milieux Heterogenes, Tanaka, JAXA, Tsukuba, Japan. (JAXA) Universities Paris 6 and Paris 7, Paris. (ESA)

Physical and Materials Sciences Selectable Optical Diagnostics Instrument – Aggregation of Colloidal Suspensions Coarsening in Solid Liquid Mixtures-2 (SODI-Colloid) will study the aggregation, or (CSLM-2) examines the kinetics of competitive mass, phenomena of colloids, which are tiny particle growth within a liquid metal matrix. solid particles suspended in a liquid, in the During this process, small particles of tin microgravity environment onboard the station. suspended in a liquid tin-lead matrix shrink by Principal investigator: Gerard Wegdam, Van losing atoms to larger particles of tin, causing der Waals-Zeeman Institute, University of the larger particles to grow, or coarsen. This Amsterdam, Amsterdam, The Netherlands. study defines the mechanisms and rates of (ESA) coarsening in the absence of gravitational settling. This work has direct applications to Two Dimensional NanoTemplate in metal alloy manufacturing on Earth, including Microgravity (2D-NanoTemplate) fabricates materials critical for aerospace applications large and highly oriented nano-scale such as the production of better aluminum two-dimensional arranged peptide arrays by alloys for turbine blades. Principal investigator: suppressing convection, sedimentation and Peter W. Voorhees, Northwestern University, buoyancy. Principal investigator: Takatoshi Evanston, Ill. (NASA) Kinoshita, Nagoya Institute of Technology, Nagoya, Aichi, Japan. (JAXA) Smoke and Aerosol Measurement Experiment (SAME) measures smoke properties, or particle Technology size distribution, of typical particles from spacecraft fire smoke to provide data to support Passive Dosimeter for Lifescience Experiment requirements for smoke detection in space and in Space (PADLES) measures radiation identify ways to improve smoke detectors on exposure levels on board the station using future spacecraft. Principal investigator: David passive and integrating dosimeters to detect Urban, Glenn Research Center, Cleveland. radiation levels. Principal investigator: Aiko (NASA) Nagamatsu, Japan Aerospace Exploration Agency, Tsukuba, Japan. (JAXA) DEvice for the study of Critical LIquids and Crystallization – High Temperature Insert For more information on the research and (DECLIC-HTI) is a multi-user facility used to technology demonstrations performed on the study transparent media and their phase International Space Station, visit transitions in microgravity onboard the http://www.nasa.gov/mission_pages/station/science/ International Space Station. The High Temperature Insert (HTI) portion of DECLIC studies water near its critical point. Principal investigators: Yves Garrabos, Institut de Chimie de la Matière Condensée de Bordeaux, France; Daniel Beysens, Physique et

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SPACE SHUTTLE DETAILED TEST toward the back of the heat shield and moving OBJECTIVES (DTO) AND DETAILED forward. Known as “tripping the boundary SUPPLEMENTARY OBJECTIVES (DSO) layer,” this phenomenon can create eddies of turbulence that, in turn, result in higher DTO 854 Boundary Layer Transition downstream heating. Flight Experiment For the experiment, a heat shield tile with a The Boundary Layer Transition (BLT) flight “speed bump” on it was installed under experiment will gather information on the effect Discovery’s left wing to intentionally disturb of high Mach number boundary layer transition the airflow in a controlled manner and make caused by a protuberance on the space shuttle the airflow turbulent. The bump is four inches during the re-entry trajectory. long and approximately 0.4 inch wide. Ten thermocouples are installed on several tiles, The experiment is designed to further including the protuberance tile and tiles understand the high Mach number thermal downstream of the protuberance. environments created by a protuberance on the lower side of the orbiter during re-entry. The Additionally, data from this experiment will protuberance was built on a BRI-18 tile expand the aerodynamics and aeroheating originally developed as a heat shield upgrade knowledge base and will be used to verify and on the orbiters. Due to the likely geometry and improve design efforts for future spacecraft. re-entry profile of future exploration vehicles, DTO 900 Solid Rocket Booster Thrust these vehicles will experience a high Mach Oscillation number boundary layer transition during atmospheric entry. By flying this protuberance The Space Shuttle Program is continuing to during the orbiter’s re-entry, a high Mach gather data on pressure oscillation, or periodic number transition environment will be created variation, a phenomenon that regularly occurs on a small zone of the orbiter’s underside, within solid rocket motors through the which will aid in gaining an improved remaining shuttle flights. The data obtained understanding of the heating in high Mach from five flights designated to acquire pressure number environments. oscillation data have provided a better understanding of solid rocket motor dynamics. STS-133 will be the fourth phase of the flight The collection of these additional data points experiment and will include data gathered on a will provide greater statistical significance of 0.5-inch tall protuberance at Mach 19 speed. the data for use in dynamic analyses of the four This protuberance height will allow engineers segment motors. These analyses and computer to collect the highest-speed boundary layer models will be used for future propulsion transition data ever experienced on the orbiter. system designs. Boundary layer transition is a disruption of the The pressure oscillation that is observed in smooth, laminar flow of supersonic air across solid rocket motors is similar to the hum made the orbiter’s belly and occurs normally when when blowing into a bottle. At 1.5 pounds per the orbiter’s velocity has dropped to around square inch, a pressure wave will move up and eight to 10 times the speed of sound, starting

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down the motor from the front to the rear, The DTO will use an advanced scientific generating acoustic noise as well as physical concepts DragonEye flash light intensification loads in the structure. These data are necessary detection and ranging (LIDAR) relative to help propulsion engineers confirm modeling navigation sensor. The DragonEye on this techniques of pressure oscillations and the mission incorporates several design and loads they create. As NASA engineers develop software improvements from the version flown alternate propulsion designs for use in NASA, earlier on STS-127 that provide increased they will take advantage of current designs performance. from which they can learn and measure. DragonEye has been baselined as SpaceX‘s In an effort to obtain data to correlate pressure primary relative navigation sensor, and it oscillation with the loads it can generate, the provides a three dimensional image based on Space Shuttle Program is continuing to use the the time of flight of a single laser pulse from the enhanced data acquisition system to gather sensor to the target and back. It provides both detailed information. range and bearing information from targets that can reflect the light back such as the DTO 701B Dragon Eye Flash LIDAR pressurized mating adapter 2 and those on the On behalf of SpaceX of Hawthorne, Calif., nadir side of station’s Japanese Kibo laboratory. NASA’s Commercial Crew and Cargo Program During departure, there will be an opportunity Office (C3PO) is sponsoring a second to image the target on the Leonardo permanent investigation of “DragonEye,” a pulsed laser multipurpose module, which is being installed navigation sensor that SpaceX’s Dragon vehicle on this shuttle mission. The DragonEye LIDAR would use to approach the International Space is eye-safe and will also be unpowered when Station. The test is to gain confidence and docked to the station, so there are no safety experience with how the DragonEye sensor concerns for spacewalks. The DragonEye DTO performs before the system is used on the will include a thermal imager as on STS-127, Dragon vehicle’s third demonstration which and a new GPS receiver. includes rendezvous with the station. The C3PO office manages the Commercial The DragonEye DTO will mount to the shuttle’s Orbital Transportation Services (COTS) projects existing trajectory control system carrier which has a Space Act Agreement with SpaceX. assembly on the orbiter’s docking system. COTS is an effort by NASA to stimulate a SpaceX will be taking data in parallel with the commercial market for spaceflight services. shuttle’s Trajectory Control Sensor (TCS) system. Both TCS and DragonEye will be While SpaceX’s recoverable Dragon spacecraft ”looking” at the retroreflectors that are on the was designed to transport crew, it will initially station. After the flight, SpaceX will compare be used to carry both pressurized and the data DragonEye collected against the data unpressurized cargo to the station. TCS collected and evaluate DragonEye’s performance.

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DTO 805 Crosswind Landing Perfor- tasks immediately after landing on a planetary mance (If opportunity) surface following prolonged spaceflight.

The purpose of this DTO is to demonstrate the To understand how changes in physiological capability to perform a manually controlled function affect functional performance, an landing in the presence of a crosswind. The interdisciplinary pre- and postflight testing testing is done in two steps. regimen called a Functional Task Test (FTT) has been developed that systematically evaluates 1. Pre-launch: Ensure planning will allow both astronaut postflight functional selection of a runway with microwave performance and related physiological changes. scanning beam landing system support, The overall objective of the FTT is to identify which is a set of dual transmitters located the key underlying physiological factors that beside the runway providing precision contribute to performance of functional tests navigation vertically, horizontally and that are representative of critical mission tasks. longitudinally with respect to the runway. This precision navigation subsystem helps This study will identify which physiological provide a higher probability of a more systems contribute the most to impaired precise landing with a crosswind of 10 to performance on each functional test. This will 15 knots as late in the flight as possible. allow us to identify the physiological systems that play the largest roles in decrements in 2. Entry: This test requires that the crew overall functional performance. Using this perform a manually controlled landing in information we can design and implement the presence of a 90-degree crosswind countermeasures that specifically target the component of 10 to 15 knots steady state. physiological systems most responsible for the altered functional performance associated with During a crosswind landing, the drag chute will spaceflight. be deployed after nose gear touchdown when the vehicle is stable and tracking the runway For more information about this and other centerline. DSOs, visit

DSO 640 Physiological Factors https://rlsda.jsc.nasa.gov/scripts/experiment/ex per.cfm?exp_index=1448 Exposure to the microgravity conditions of spaceflight causes astronauts to experience and alterations in multiple physiological systems. These physiological changes include https://rlsda.jsc.nasa.gov/docs/research/researc sensorimotor disturbances, cardiovascular h_detail.cfm?experiment_type_code=35&resear deconditioning and loss of muscle mass and chtype= strength. These changes might affect the ability

of crew members to perform critical mission

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HISTORY OF SPACE SHUTTLE DISCOVERY

Space shuttle Discovery ends its spaceflight servicing missions (STS-82 in February 1997 career with more missions than any other and STS-103 in December 1999). vehicle in the fleet; serving as a symbol of American pride and leadership in human During its many successful trips to space, spaceflight. Discovery has carried satellites aloft, ferried modules and crew to the International Space Discovery was launched on its maiden voyage Station, and provided the setting for countless (STS-41D) on Aug. 30, 1984 and since has scientific experiments. completed 38 missions. It was the third orbital vehicle manufactured following Columbia and UPGRADES AND FEATURES Challenger. Just like all of the orbiters, Discovery has Construction of Discovery began in August undergone some major modifications over the 1979 at the Palmdale, Calif. manufacturing years. The most recent began in 2002 and was plant. Designated OV-103, it was transported the first carried out at Kennedy. It provided to Kennedy Space Center in November 1983 99 upgrades and 88 special tests, including new ahead of its maiden voyage. changes to make it safer for flight. BACKGROUND Discovery had the distinction of being chosen as the “Return to Flight” orbiter twice. The first The choice of the name “Discovery” carried on was for STS-26 in 1988, and the second when it a tradition drawn from some historic, carried the STS-114 crew on its mission to the Earth-bound exploring ships of the past. One International Space Station in July 2005. of these sailing forerunners was the vessel used in the early 1600s by Henry Hudson to explore Discovery benefited from lessons learned in the Hudson Bay and search for a northwest construction and testing of Enterprise, passage from the Atlantic to the Pacific. Columbia and Challenger. At rollout, its weight was some 6,870 pounds less than Another such ship was used by British explorer Columbia. James Cook in the 1770s during his voyages in the South Pacific, leading to the discovery of the Beginning in the fall of 1995, the orbiter Hawaiian Islands. In addition, two British underwent a nine-month orbiter maintenance Royal Geographical Society ships have carried down period in Palmdale, Calif. during which the name “Discovery” as they sailed on it was outfitted with a fifth set of cryogenic expeditions to the North Pole and the Antarctic. tanks and an external airlock to support missions to the International Space Station. It Destined for exploring the heavens instead of returned to Kennedy, atop its Boeing 747 the seas, it was only fitting that NASA’s shuttle carrier aircraft, in June 1996. Discovery carried the Hubble Space Telescope into space during mission STS-31 in April 1990, Following STS-105, Discovery became the first and provided both the second and third Hubble of the orbiter fleet to undergo an orbiter major

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modification period at Kennedy. Work began July 16, 1982 in September 2002, and along with the Upper forward fuselage on dock, Palmdale scheduled upgrades, additional safety modifications were added as part of the Aug. 5, 1982 preparations for the 2005 Return to Flight Vertical stabilizer on dock, Palmdale mission. Sept. 3, 1982 CONSTRUCTION MILESTONES Start of final assembly Oct. 15, 1982 Jan. 29, 1979 Body flap on dock, Palmdale Contract Award Jan. 11, 1983 Aug. 27, 1979 Aft fuselage on dock, Palmdale Start long lead fabrication of crew module Feb. 25, 1983 June 20, 1980 Complete final assembly and closeout Start fabrication lower fuselage installation, Palmdale Nov. 10, 1980 Feb. 28, 1983 Start structural assembly of aft fuselage Start initial subsystems test, power-on, Dec. 8, 1980 Palmdale Start initial system installation aft fuselage May 13, 1983 March 2, 1981 Complete initial subsystems testing Start fabrication/assembly of payload bay doors July 26, 1983 Oct. 26, 1981 Complete subsystems testing Start initial system installation, crew module, Aug. 12, 1983 Downey Completed final acceptance Jan. 4, 1982 Oct. 16, 1983 Start initial system installation upper forward Rollout from Palmdale fuselage Nov. 5, 1983 March 16, 1982 Overland transport from Palmdale to Edwards Midfuselage on dock, Palmdale Air Force Base, Calif. March 30, 1982 Nov. 9, 1983 Elevons on dock, Palmdale Delivery to Kennedy Space Center April 30, 1982 June 2, 1984 Wings arrive at Palmdale from Grumman Flight readiness firing April 30, 1982 Lower forward fuselage on dock, Palmdale

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Aug. 30, 1984 16. STS-56 (April 9-17, 1993) First flight (STS-41-D) 3,853,997 miles 17. STS-51 (Sept. 12-22, 1993) Nov. 1, 2010 4,106,411 miles Final scheduled flight (STS-133) 18. STS-60 (Feb. 3-11, 1994) FLIGHT MILESTONES 3,439,704 miles 1. STS-41D (Aug. 30 – Sept. 5, 1984) 19. STS-64 (Sept. 9-20, 1994) 2,210,000 miles 4,576,174 miles 2. STS-51A (Nov. 8-16, 1984) 20. STS-63 (Feb. 2-11, 1995) 2,870,000 miles 2,922,000 miles 3. STS-51C (Jan. 24-27, 1985) 21. STS-70 (July 13-22, 1995) 1,242,566 miles 3,700,000 miles 4. STS-51D (April 12-19, 1985) 22. STS-82 (Feb. 11-21, 1997) 2,889,785 miles 3,800,000 miles 5. STS-51G (June 17-24, 1985) 23. STS-85 (Aug. 7-19, 1997) 2,916,127 miles 4,725,000 miles 6. STS-51I (Aug. 27 – Sept. 3, 1985) 2,500,000 miles 24. STS-91 (June 2-12, 1998) 3,800,000 miles 7. STS-26 (Sept. 29 – Oct. 3, 1988) 25. STS-95 (Oct. 29 – Nov. 7, 1998) 1,430,505 miles 3,644,459 miles 8. STS-29 (March 13-18, 1989) 26. STS-96 (May 27 – June 6, 1999) 1,800,000 miles 4,051,000 miles 9. STS-33 (Nov. 22-27, 1989) 27. STS-103 (Dec. 19-27, 1999) 2,045,056 miles 3,267,360 miles 10. STS-31 (April 24-29, 1990) 28. STS-92 (Oct. 11-24, 2000) 2,068,213 miles 5,331,301 miles 11. STS-41 (Oct. 6-10, 1990) 1,707,445 miles 29. STS-102 (March 8-21, 2001) 5,357,432 miles 12. STS-39 (April 28 – May 6, 1991) 30. STS-105 (Aug. 10-22, 2002) 3,475,000 miles 4,912,389 miles 13. STS-48 (Sept. 12-18, 1991) 2,193,670 miles 31. STS-114 (July 26 – Aug. 9, 2005) 5,796,419 miles 14. STS-42 (Jan. 22-30, 1992) 3,349,830 miles 32. STS-121 (July 4-17, 2006) 15. STS-53 (Dec.2-9, 1992) 5,293,923 miles 3,034,680 miles

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33. STS-116 (Dec. 9-22, 2006) DISCOVERY BY THE NUMBERS 5,330,398 miles Discovery miles 142,917,535 (through 34. STS-120 (Oct. 23 – Nov. 7, 2007) traveled STS-131) 6,249,432 miles Days in orbit 352 (8,441 hours, 50 35. STS-124 (May 31 – June 14, 2008) minutes, 41 seconds) 5,735,643 miles Orbits 5,628

36. STS-119 (March 15-28, 2009) Flights 38 (through STS-131) 5,304,106 miles 37. STS-128 (Aug. 28 – Sept. 11, 2009) Individual crew 180 (through STS-131) 5,755,275 miles members

38. STS-131 (April 5-20, 2010) Russian Mir space 1 (STS-91 June 1998) 6,232,235 miles station dockings

39. STS-133 (Nov. 1-12, 2010) International Space 12 (through STS-131) Approx. 4.5 million miles Station dockings

Total Discovery Miles 142,917,535 (through STS-131)

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SHUTTLE REFERENCE DATA

SHUTTLE ABORT MODES launch site, KSC, approximately 25 minutes after liftoff. Redundant Set Launch Sequencer (RSLS) Aborts The RTLS profile is designed to accommodate the loss of thrust from one space shuttle main These occur when the onboard shuttle engine between liftoff and approximately computers detect a problem and command a four minutes 20 seconds, after which not halt in the launch sequence after taking over enough main propulsion system propellant from the ground launch sequencer and before remains to return to the launch site. An RTLS solid rocket booster ignition. can be considered to consist of three stages – a Ascent Aborts powered stage, during which the space shuttle main engines are still thrusting; an external Selection of an ascent abort mode may become tank separation phase; and the glide phase, necessary if there is a failure that affects vehicle during which the orbiter glides to a landing at performance, such as the failure of a space the KSC. The powered RTLS phase begins with shuttle main engine or an orbital maneuvering the crew selection of the RTLS abort, after solid system engine. Other failures requiring early rocket booster separation. The crew selects the termination of a flight, such as a cabin leak, abort mode by positioning the abort rotary might also require the selection of an abort switch to RTLS and depressing the abort push mode. There are two basic types of ascent abort button. The time at which the RTLS is selected modes for space shuttle missions: intact aborts depends on the reason for the abort. For and contingency aborts. Intact aborts are example, a three-engine RTLS is selected at the designed to provide a safe return of the orbiter last moment, about 3 minutes, 34 seconds into to a planned landing site. Contingency aborts the mission; whereas an RTLS chosen due to an are designed to permit flight crew survival engine out at liftoff is selected at the earliest following more severe failures when an intact time, about 2 minutes, 20 seconds into the abort is not possible. A contingency abort mission (after solid rocket booster separation). would generally result in a ditch operation. After RTLS is selected, the vehicle continues Intact Aborts downrange to dissipate excess main propulsion There are four types of intact aborts: abort to system propellant. The goal is to leave only orbit (ATO), abort once around (AOA), enough main propulsion system propellant to transoceanic abort landing (TAL) and be able to turn the vehicle around, fly back return to launch site (RTLS). toward KSC and achieve the proper main engine cutoff conditions so the vehicle can Return to Launch Site glide to KSC after external tank separation. The RTLS abort mode is designed to allow the During the downrange phase, a pitch-around return of the orbiter, crew, and payload to the maneuver is initiated (the time depends in part on the time of a space shuttle main engine

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failure) to orient the orbiter/external tank pressure leak or cooling system failure, occurs configuration to a heads-up attitude, pointing after the last RTLS opportunity, making it toward the launch site. At this time, the vehicle imperative to land as quickly as possible. is still moving away from the launch site, but the space shuttle main engines are now In a TAL abort, the vehicle continues on a thrusting to null the downrange velocity. In ballistic trajectory across the Atlantic Ocean to addition, excess orbital maneuvering system land at a predetermined runway. Landing and reaction control system propellants are occurs about 45 minutes after launch. The dumped by the continuous orbital landing site is selected near the normal ascent maneuvering system and reaction control ground track of the orbiter to make the most system engine thrustings to improve the orbiter efficient use of space shuttle main engine weight and center of gravity for the glide phase propellant. The landing site also must have the and landing. necessary runway length, weather conditions and U.S. State Department approval. The three The vehicle will reach the desired main engine landing sites that have been identified for a cutoff point with less than 2 percent excess launch are Zaragoza, Spain; Morón, Spain; and propellant remaining in the external tank. At Istres, France. main engine cutoff minus 20 seconds, a pitch down maneuver (called powered pitch-down) To select the TAL abort mode, the crew must takes the mated vehicle to the required external place the abort rotary switch in the TAL/AOA tank separation attitude and pitch rate. After position and depress the abort push button main engine cutoff has been commanded, the before main engine cutoff (depressing it after external tank separation sequence begins, main engine cutoff selects the AOA abort including a reaction control system maneuver mode). The TAL abort mode begins sending that ensures that the orbiter does not recontact commands to steer the vehicle toward the plane the external tank and that the orbiter has of the landing site. It also rolls the vehicle achieved the necessary pitch attitude to begin heads up before main engine cutoff and sends the glide phase of the RTLS. commands to begin an orbital maneuvering system propellant dump (by burning the After the reaction control system maneuver has propellants through the orbital maneuvering been completed, the glide phase of the RTLS system engines and the reaction control system begins. From then on, the RTLS is handled engines). This dump is necessary to increase similarly to a normal entry. vehicle performance (by decreasing weight) to place the center of gravity in the proper place Transoceanic Abort Landing for vehicle control and to decrease the vehicle’s The TAL abort mode was developed to landing weight. TAL is handled like a normal improve the options available if a space shuttle entry. main engine fails after the last RTLS Abort to Orbit opportunity but before the first time that an AOA can be accomplished with only two space An ATO is an abort mode used to boost the shuttle main engines or when a major orbiter orbiter to a safe orbital altitude when system failure, for example, a large cabin performance has been lost and it is impossible

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to reach the planned orbital altitude. If a space would maintain orbiter integrity for in-flight shuttle main engine fails in a region that results crew escape if a landing cannot be achieved at a in a main engine cutoff under speed, the suitable landing field. MCC will determine that an abort mode is necessary and will inform the crew. The orbital Contingency aborts due to system failures other maneuvering system engines would be used to than those involving the main engines would place the orbiter in a circular orbit. normally result in an intact recovery of vehicle and crew. Loss of more than one main engine Abort Once Around may, depending on engine failure times, result in a safe runway landing. However, in most The AOA abort mode is used in cases in which three-engine-out cases during ascent, the vehicle performance has been lost to such an orbiter would have to be ditched. The inflight extent that either it is impossible to achieve a crew escape system would be used before viable orbit or not enough orbital maneuvering ditching the orbiter. system propellant is available to accomplish the orbital maneuvering system thrusting Abort Decisions maneuver to place the orbiter in space. In addition, an AOA is used in cases in which a There is a definite order of preference for the major systems problem (cabin leak, loss of various abort modes. The type of failure and the cooling) makes it necessary to land quickly. In time of the failure determine which type of abort the AOA abort mode, one orbital maneuvering is selected. In cases where performance loss is system thrusting sequence is made to adjust the the only factor, the preferred modes are ATO, post-main engine cutoff orbit so a second AOA, TAL and RTLS, in that order. The mode orbital maneuvering system thrusting sequence chosen is the highest one that can be completed will result in the vehicle deorbiting and landing with the remaining vehicle performance. at the AOA landing site (White Sands, N.M.; In the case of some support system failures, Edwards Air Force Base, Calif.; or the Kennedy such as cabin leaks or vehicle cooling problems, Space Center, Fla). Thus, an AOA results in the the preferred mode might be the one that will orbiter circling the Earth once and landing end the mission most quickly. In these cases, about 90 minutes after liftoff. TAL or RTLS might be preferable to AOA or After the deorbit thrusting sequence has been ATO. A contingency abort is never chosen if executed, the flight crew flies to a landing at the another abort option exists. planned site much as it would for a nominal Mission Control Houston is prime for calling entry. these aborts because it has a more precise Contingency Aborts knowledge of the orbiter’s position than the crew can obtain from onboard systems. Before Contingency aborts are caused by loss of more main engine cutoff, Mission Control makes than one main engine or failures in other periodic calls to the crew to identify which systems. Loss of one main engine while abort mode is (or is not) available. If ground another is stuck at a low thrust setting also may communications are lost, the flight crew has necessitate a contingency abort. Such an abort onboard methods, such as cue cards, dedicated

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displays and display information, to determine (STS-55) March 22, 1993 the abort region. Which abort mode is selected The countdown for Columbia’s launch was depends on the cause and timing of the failure halted by onboard computers at T-3 seconds causing the abort and which mode is safest or following a problem with purge pressure improves mission success. If the problem is a readings in the oxidizer preburner on main space shuttle main engine failure, the flight engine No. 2. Columbia’s three main engines crew and Mission Control Center select the best were replaced on the launch pad, and the flight option available at the time a main engine fails. was rescheduled behind Discovery’s launch If the problem is a system failure that on STS-56. Columbia finally launched on jeopardizes the vehicle, the fastest abort mode April 26, 1993. that results in the earliest vehicle landing is (STS-51) Aug. 12, 1993 chosen. RTLS and TAL are the quickest options (35 minutes), whereas an AOA requires about The countdown for Discovery’s third launch 90 minutes. Which of these is selected depends attempt ended at the T-3 second mark when on the time of the failure with three good space onboard computers detected the failure of one shuttle main engines. of four sensors in main engine No. 2 which monitor the flow of hydrogen fuel to the The flight crew selects the abort mode by engine. All of Discovery’s main engines were positioning an abort mode switch and ordered replaced on the launch pad, delaying depressing an abort push button. the shuttle’s fourth launch attempt until SHUTTLE ABORT HISTORY Sept. 12, 1993. RSLS Abort History (STS-68) Aug. 18, 1994 (STS-41 D) June 26, 1984 The countdown for Endeavour’s first launch attempt ended 1.9 seconds before liftoff when The countdown for the second launch attempt onboard computers detected higher than for Discovery’s maiden flight ended at T-4 acceptable readings in one channel of a sensor seconds when the orbiter’s computers detected monitoring the discharge temperature of the a sluggish valve in main engine No. 3. The high pressure oxidizer turbopump in main main engine was replaced and Discovery was engine No. 3. A test firing of the engine at the finally launched on Aug. 30, 1984. Stennis Space Center in Mississippi on (STS-51 F) July 12, 1985 Sept. 2, 1994, confirmed that a slight drift in a fuel flow meter in the engine caused a slight The countdown for Challenger’s launch was increase in the turbopump’s temperature. The halted at T-3 seconds when onboard computers test firing also confirmed a slightly slower start detected a problem with a coolant valve on for main engine No. 3 during the pad abort, main engine No. 2. The valve was replaced and which could have contributed to the higher Challenger was launched on July 29, 1985. temperatures. After Endeavour was brought back to the Vehicle Assembly Building to be outfitted with three replacement engines,

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NASA managers set Oct. 2, 1994, as the date for shuttle, traveling at about 17,000 miles per Endeavour’s second launch attempt. hour, reaches orbit.

Abort to Orbit History The main engine operates at greater temperature extremes than any mechanical (STS-51 F) July 29, 1985 system in common use today. The fuel, After an RSLS abort on July 12, 1985, liquefied hydrogen at -423 degrees Fahrenheit, Challenger was launched on July 29, 1985. is the second coldest liquid on Earth. When it Five minutes and 45 seconds after launch, a and the liquid oxygen are combusted, the sensor problem resulted in the shutdown of temperature in the main combustion chamber is center engine No. 1, resulting in a safe “abort to 6,000 degrees Fahrenheit, hotter than the orbit” and successful completion of the mission. boiling point of iron. SPACE SHUTTLE MAIN ENGINES The main engines use a staged combustion cycle so that all propellants entering the engines Developed in the 1970s by NASA’s Marshall are used to produce thrust, or power, more Space Flight Center, in Huntsville, Ala., the efficiently than any previous rocket engine. In space shuttle main engine is the most advanced a staged combustion cycle, propellants are first liquid-fueled rocket engine ever built. Every burned partially at high pressure and relatively space shuttle main engine is tested and proven low temperature, and then burned completely flight worthy at NASA’s Stennis Space Center at high temperature and pressure in the main in south Mississippi, before installation on combustion chamber. The rapid mixing of the an orbiter. Its main features include variable propellants under these conditions is so thrust, high performance reusability, high complete that 99 percent of the fuel is burned. redundancy and a fully integrated engine controller. At normal operating level, each engine generates 490,847 pounds of thrust, measured The shuttle’s three main engines are mounted in a vacuum. Full power is 512,900 pounds of on the orbiter aft fuselage in a triangular thrust; minimum power is 316,100 pounds of pattern. Spaced so that they are movable thrust. during launch, the engines are used, in conjunction with the solid rocket boosters, to The engine can be throttled by varying the steer the shuttle vehicle. output of the preburners, thus varying the speed of the high-pressure turbopumps and, Each of these powerful main engines is 14 feet therefore, the flow of the propellant. long, weighs about 7,000 pounds and is 7.5 feet in diameter at the end of its nozzle. At about 26 seconds into ascent, the main engines are throttled down to 316,000 pounds The engines operate for about 8.5 minutes of thrust to keep the dynamic pressure on the during liftoff and ascent, burning more than vehicle below a specified level, about 500,000 gallons of super-cold liquid hydrogen 580 pounds per square foot, known as max q. and liquid oxygen propellants stored in the Then, the engines are throttled back up to external tank attached to the underside of the normal operating level at about 60 seconds. shuttle. The engines shut down just before the This reduces stress on the vehicle. The main

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engines are throttled down again at about by reducing pressure and temperature in the seven minutes, 40 seconds into the mission to chamber. maintain three g’s, three times the Earth’s The most recent engine enhancement is the gravitational pull, reducing stress on the crew advanced health management system (AHMS), and the vehicle. This acceleration level is about which made its first flight in 2007. AHMS is a one-third the acceleration experienced on controller upgrade that provides new previous crewed space vehicles. monitoring and insight into the health of the About 10 seconds before main engine cutoff two most complex components of the space (MECO), the cutoff sequence begins. About shuttle main engine – the high pressure fuel three seconds later the main engines are turbopump and the high pressure oxidizer commanded to begin throttling at 10 percent turbopump. New advanced digital signal thrust per second until they achieve 65 percent processors monitor engine vibration and have thrust. This is held for about 6.7 seconds, and the ability to shut down an engine if vibration the engines are shut down. exceeds safe limits. AHMS was developed by engineers at Marshall. The engine performance has the highest thrust for its weight of any engine yet developed. In After the orbiter lands, the engines are removed fact, one space shuttle main engine generates and returned to a processing facility at NASA’s sufficient thrust to maintain the flight of two Kennedy Space Center, Fla., where they are and one-half Boeing 747 airplanes. rechecked and readied for the next flight. Some components are returned to the main engine’s The space shuttle main engine also is the first prime contractor, Pratt & Whitney Rocketdyne, rocket engine to use a built-in electronic digital West Palm Beach, Fla., for regular maintenance. controller, or computer. The controller accepts The main engines are designed to operate for commands from the orbiter for engine start, 7.5 accumulated hours. change in throttle, shutdown and monitoring of engine operation. SPACE SHUTTLE SOLID ROCKET NASA continues to increase the reliability and BOOSTERS (SRB) safety of shuttle flights through a series of The two solid rocket boosters (SRBs) required enhancements to the space shuttle main for a space shuttle launch and first two minutes engines. The engines were modified in 1988, of powered flight boast the largest 1995, 1998, 2001 and 2007. Modifications solid-propellant motors ever flown. They are include new high-pressure fuel and oxidizer the first large rockets designed for reuse and turbopumps that reduce maintenance and are the only solid rocket motors rated for operating costs of the engine, a two-duct human flight. The SRBs have the capacity to powerhead that reduces pressure and carry the entire weight of the external fuel tank turbulence in the engine, and a single-coil heat (ET), and orbiter, and to transmit the weight exchanger that lowers the number of post flight load through their structure to the mobile inspections required. Another modification launcher platform (MLP). incorporates a large-throat main combustion chamber that improves the engine’s reliability

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The SRBs provide 71.4 percent of the thrust They are attached to the ET at the SRB aft attach required to lift the space shuttle off the launch ring by an upper and lower attach strut and a pad and during first-stage ascent to an altitude diagonal attach strut. The forward end of each of about 150,000 feet, or 28 miles. At launch, SRB is affixed to the ET by one attach bolt and each booster has a sea level thrust of ET ball fitting on the forward skirt. While approximately 3.3 million pounds and is positioned on the launch pad, the space shuttle ignited after the ignition and verification of the is attached to the MLP by four bolts and three space shuttle main engines (SSMEs). explosive nuts equally spaced around each SRB. After ignition of the solid rocket motors, the SRB apogee occurs at an altitude of about nuts are severed by small explosives that allow 230,000 feet, or 43 miles, 75 seconds after the space shuttle vehicle to perform lift off. separation from the main vehicle. At booster separation, the space shuttle orbiter has reached United Space Alliance an altitude of 24 miles and is traveling at a United Space Alliance (USA), at Kennedy speed in excess of 3,000 miles per hour. facilities, is responsible for all SRB operations, The primary elements of each booster are nose except the motor and nozzle portions. cap, housing the pilot and drogue parachute; In conjunction with maintaining sole frustum, housing the three main parachutes in responsibility for manufacturing and a cluster; forward skirt, housing the booster processing of the nonmotor hardware and flight avionics, altitude sensing, recovery vehicle integration, USA provides the service of avionics, parachute cameras and range safety retrieval, post flight inspection and analysis, destruct system; four motor segments, disassembly and refurbishment of the containing the solid propellant; motor nozzle; hardware. USA also exclusively retains and aft skirt, housing the nozzle and thrust comprehensive responsibility for the orbiter. vector control systems required for guidance. The reusable solid rocket motor segments are Each SRB possesses its own redundant shipped from ATK Launch Systems in Utah to auxiliary power units and hydraulic pumps. Kennedy, where they are mated by USA SRB impact occurs in the ocean approximately personnel to the other structural components – 140 miles downrange. SRB retrieval is the forward assembly, aft skirt, frustum and provided after each flight by specifically nose cap – in the Vehicle Assembly Building. designed and built ships. The frustums, Work involves the complete disassembly and drogue and main parachutes are loaded onto refurbishment of the major SRB structures – the the ships along with the boosters and towed aft skirts, frustums, forward skirts and all back to NASA’s Kennedy Space Center, where ancillary hardware – required to complete an they are disassembled and refurbished for SRB stack and mate to the ET. Work then reuse. Before retirement, each booster can be proceeds to ET/SRB mate, mate with the orbiter used as many as 20 times. and finally, space shuttle close out operations. After hardware restoration concerning flight Each booster is just over 149 feet long and configuration is complete, automated checkout 12.17 feet in diameter. Both boosters have a and hot fire are performed early in hardware combined weight of 1,303,314 pounds at lift-off.

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flow to ensure that the refurbished components contains sand to absorb the shock of the bolt satisfy all flight performance requirements. dropping down several feet. The SRB bolt is 28 inches long, 3.5 inches in diameter and ATK Launch Systems (ATK) weighs approximately 90 pounds. The ATK Launch Systems of Brigham City, Utah, frangible nut is captured in a blast container on manufactures space shuttle reusable solid the aft skirt specifically designed to absorb the rocket motors (RSRMs), at their Utah facility. impact and prevent pieces of the nut from Each RSRM – just over 126 feet long and 12 feet liberating and becoming debris that could in diameter – consists of four rocket motor damage the space shuttle. segments and an aft exit cone assembly is. Integrated Electronic Assembly From ignition to end of burn, each RSRM generates an average thrust of 2.6 million The aft integrated electronic assembly (IEA), pounds and burns for approximately mounted in the ET/SRB attach ring, provides 123 seconds. Of the motor’s total weight of the electrical interface between the SRB systems 1.25 million pounds, propellant accounts for and the obiter. The aft IEA receives data, 1.1 million pounds. The four motor segments commands, and electrical power from the are matched by loading each from the same orbiter and distributes these inputs throughout batches of propellant ingredients to minimize each SRB. Components located in the forward any thrust imbalance. The segmented casing assemblies of each SRB are powered by the aft design assures maximum flexibility in IEA through the forward IEA, except for those fabrication and ease of transportation and utilizing the recovery and range safety batteries handling. Each segment is shipped to KSC on a located in the forward assemblies. The forward heavy-duty rail car with a specialty built cover. IEA communicates with and receives power from the orbiter through the aft IEA, but has no SRB Hardware Design Summary direct electrical connection to the orbiter. Hold-Down Posts Electrical Power Distribution

Each SRB has four hold-down posts that fit into Electrical power distribution in each SRB corresponding support posts on the MLP. consists of orbiter-supplied main dc bus power Hold-down bolts secure the SRB and MLP posts to each SRB via SRB buses A, B and C. Orbiter together. Each bolt has a nut at each end, but main dc buses A, B and C supply main dc bus the top nut is frangible, or breakable. The top power to corresponding SRB buses A, B and C. nut contains two NASA standard detonators In addition, orbiter main dc, bus C supplies (NSDs), that, when ignited at solid rocket motor backup power to SRB buses A and B, and ignition command, split the upper nut in half. orbiter bus B supplies backup power to Splitting the upper nuts allow the hold-down SRB bus C. This electrical power distribution bolts to be released and travel downward arrangement allows all SRB buses to remain because of NSD gas pressure, gravity and the powered in the event one orbiter main bus fails. release of tension in the bolt, which is The nominal dc voltage is 28 V dc, with an pretensioned before launch. The bolt is upper limit of 32 V dc and a lower limit of stopped by the stud deceleration stand which 24 V dc.

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Hydraulic Power Units is greater than the bypass line’s, at which point all the fuel is supplied to the fuel pump. There are two self-contained, independent hydraulic power units (HPUs) on each SRB. The APU turbine assembly provides Each HPU consists of an auxiliary power unit mechanical power to the APU gearbox, which (APU); fuel supply module (FSM); hydraulic drives the APU fuel pump, hydraulic pump pump; hydraulic reservoir; and hydraulic fluid and lube oil pump. The APU lube oil pump manifold assembly. The APUs are fueled by lubricates the gearbox. The turbine exhaust of hydrazine and generate mechanical shaft power each APU flows over the exterior of the gas to a hydraulic pump that produces hydraulic generator, cooling it and directing it overboard pressure for the SRB hydraulic system. The through an exhaust duct. APU controller electronics are located in the SRB aft integrated electronic assemblies on the When the APU speed reaches 100 percent, the aft ET attach rings. The two separate HPUs APU primary control valve closes and the and two hydraulic systems are located inside APU speed is controlled by the APU controller the aft skirt of each SRB between the SRB electronics. If the primary control valve logic nozzle and skirt. The HPU components are fails to the open state, the secondary control mounted on the aft skirt between the rock and valve assumes control of the APU at tilt actuators. The two systems operate from 112 percent speed. Each HPU on an SRB is T minus 28 seconds until SRB separation from connected to both servoactuators. One HPU the orbiter and ET. The two independent serves as the primary hydraulic source for the hydraulic systems are connected to the rock servoactuator and the other HPU serves as the and tilt servoactuators. secondary hydraulics for the servoactuator. Each servoactuator has a switching valve that The HPUs and their fuel systems are isolated allows the secondary hydraulics to power the from each other. Each fuel supply module, or actuator if the primary hydraulic pressure tank, contains 22 pounds of hydrazine. The drops below 2,050 psi. A switch contact on the fuel tank is pressurized with gaseous nitrogen switching valve will close when the valve is in at 400 psi to provide the force to expel via the secondary position. When the valve is positive expulsion the fuel from the tank to the closed, a signal is sent to the APU controller fuel distribution line. A positive fuel supply to that inhibits the 100 percent APU speed control the APU throughout its operation is logic and enables the 112 percent APU speed maintained. control logic. The 100 percent APU speed enables one APU/HPU to supply sufficient The fuel isolation valve is opened at APU operating hydraulic pressure to both startup to allow fuel to flow to the APU fuel servoactuators of that SRB. pump and control valves and then to the gas generator. The gas generator’s catalytic action The APU 100 percent speed corresponds to decomposes the fuel and creates a hot gas. It 72,000 rpm, 110 percent to 79,200 rpm and feeds the hot gas exhaust product to the APU 112 percent to 80,640 rpm. two-stage gas turbine. Fuel flows primarily through the startup bypass line until the APU The hydraulic pump speed is 3,600 rpm and speed is such that the fuel pump outlet pressure supplies hydraulic pressure of 3,050, plus or

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minus 50 psi. A high-pressure relief valve position the power spool. With four identical provides overpressure protection to the commands to the four servovalves, the actuator hydraulic system and relieves at 3,750 psi. force-sum action prevents a single erroneous command from affecting power ram motion. If The APUs/HPUs and hydraulic systems are the erroneous command persists for more than reusable for 20 missions. a predetermined time, differential pressure Thrust Vector Control sensing activates a selector valve to isolate and remove the defective servovalve hydraulic Each SRB has two hydraulic gimbal pressure. This permits the remaining channels servoactuators: one for rock and one for tilt. and servovalves to control the actuator ram The servoactuators provide the force and spool. control to gimbal the nozzle for thrust vector control (TVC). The all-axis gimbaling capability Failure monitors are provided for each channel is 8 degrees. Each nozzle has a carbon cloth to indicate which channel has been bypassed. liner that erodes and chars during firing. The An isolation valve on each channel provides the nozzle is a convergent-divergent, movable capability of resetting a failed or bypassed design in which an aft pivot-point flexible channel. bearing is the gimbal mechanism. Each actuator ram is equipped with transducers The space shuttle ascent TVC portion of the for position feedback to the thrust vector flight control system directs the thrust of the control system. Within each servoactuator ram three SSMEs and the two SRB nozzles to control is a splashdown load relief assembly to cushion shuttle attitude and trajectory during liftoff and the nozzle at water splashdown and prevent ascent. Commands from the guidance system damage to the nozzle flexible bearing. are transmitted to the ascent TVC, or ATVC, SRB Rate Gyro Assemblies drivers, which transmit signals proportional to the commands to each servoactuator of the Each SRB contains two rate gyro assemblies main engines and SRBs. Four independent (RGAs) mounted in the forward skirt flight control system channels and four ATVC watertight compartment. Each RGA contains channels control six main engine and four two orthogonally mounted gyroscopes – pitch SRB ATVC drivers, with each driver controlling and yaw axes. In conjunction with the orbiter one hydraulic port on each main and SRB roll rate gyros, they provide angular rate servoactuator. information that describes the inertial motion of the vehicle cluster to the orbiter computers and Each SRB servoactuator consists of four the guidance, navigation and control system independent, two-stage servovalves that during first stage ascent to SRB separation. At receive signals from the drivers. Each SRB separation, all guidance control data is servovalve controls one power spool in each handed off from the SRB RGAs to the orbiter actuator, which positions an actuator ram and RGAs. The RGAs are designed and qualified the nozzle to control the direction of thrust. for 20 missions. The four servovalves in each actuator provide a force-summed majority voting arrangement to

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Propellant the pyro firing output. These signals – arm, fire 1 and fire 2 – originate in the orbiter The propellant mixture in each SRB motor general-purpose computers and are transmitted consists of ammonium perchlorate, an oxidizer, to the MECs. The MECs reformat them to 28 V 69.6 percent by weight; aluminum, a fuel, dc signals for the PICs. The arm signal charges 16 percent by weight; iron oxide, a catalyst, the PIC capacitor to 40 V dc, minimum 20 V dc. 0.4 percent by weight; polymer, a binder that holds the mixture together, 12.04 percent by The fire 2 commands cause the redundant weight; and epoxy curing agent, 1.96 percent NSDs to fire through a thin barrier seal down a by weight. The propellant is an 11-point flame tunnel. This ignites a pyro booster star-shaped perforation in the forward motor charge, which is retained in the safe and arm segment and a double truncated cone device behind a perforated plate. The booster perforation in each of the aft segments and aft charge ignites the propellant in the igniter closure. This configuration provides high initiator; and combustion products of this thrust at ignition and then reduces the thrust by propellant ignite the solid rocket motor igniter, about one-third 50 seconds after liftoff to which fires down the length of the solid rocket prevent overstressing the vehicle during motor igniting the solid rocket motor maximum dynamic pressure. propellant.

SRB Ignition The general purpose computer (GPC) launch sequence also controls certain critical main SRB ignition can occur only when a manual propulsion system valves and monitors the lock pin from each SRB safe and arm device has engine-ready indications from the SSMEs. The been removed by the ground crew during main propulsion system (MPS) start commands prelaunch activities. At T minus 5 minutes, the are issued by the on-board computers at SRB safe and arm device is rotated to the arm T minus 6.6 seconds. There is a staggered start position. The solid rocket motor ignition – engine three, engine two, engine one – within commands are issued when the three SSMEs 0.25 of a second, and the sequence monitors the are at or above 90 percent rated thrust; no thrust buildup of each engine. All three SSMEs SSME fail and/or SRB ignition pyrotechnic must reach the required 90 percent thrust initiator controller (PIC) low voltage is within three seconds; otherwise, an orderly indicated; and there are no holds from the shutdown is commanded and safing functions launch processing system (LPS). are initiated. The solid rocket motor ignition commands are Normal thrust buildup to the required sent by the orbiter computers through the 90 percent thrust level will result in the master events controllers (MECs) to the NSDs SSMEs being commanded to the liftoff position installed in the safe and arm device in each at T-minus 3 (T - 3) seconds as well as the SRB. A pyrotechnic initiation controller (PIC) is fire 1 command being issued to arm the SRBs. a single-channel capacitor discharge At T - 3 seconds, the vehicle base bending load device that controls the firing of each modes are allowed to initialize. pyrotechnic device. Three signals must be present simultaneously for the PIC to generate

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At T - 0, the two SRBs are ignited by the The aft attachment points consist of three four orbiter on-board computers; commands separate struts: upper, diagonal, and lower. are sent to release the SRBs; the two T - 0 Each strut contains one bolt with an NSD umbilicals, one on each side of the spacecraft, pressure cartridge at each end. The upper strut are retracted; the onboard master timing unit, also carries the umbilical interface between its event timer and mission event timers are SRB and the external tank and on to the orbiter. started; the three SSMEs are at 100 percent; and Redesigned Booster Separation Motors (RBSM) the ground launch sequence is terminated.

SRB Separation Eight Booster Separation Motors (BSMs), are located on each booster – four on the forward The SRB/ET separation subsystem provides for section and four on the aft skirt. BSMs provide separation of the SRBs from the orbiter/ET the force required to push the SRBs away from without damage to or recontact of the elements the orbiter/ET at separation. Each BSM weighs – SRBs, orbiter/ET – during or after separation approximately 165 pounds and is 31.1 inches for nominal modes. SRB separation is initiated long and 12.8 inches in diameter. Once the when the three solid rocket motor chamber SRBs have completed their flight, the BSMs are pressure transducers are processed in the fired to jettison the SRBs away from the orbiter redundancy management middle value select and external tank, allowing the boosters to and the head end chamber pressure of both parachute to Earth and be reused. The BSMs in SRBs is less than or equal to 50 psi. A backup each cluster of four are ignited by firing cue is the time elapsed from booster ignition. redundant NSD pressure cartridges into redundant confined detonating fuse manifolds. The separation sequence is initiated, The separation commands issued from the commanding the thrust vector control actuators orbiter by the SRB separation sequence initiate to the null position and putting the main the redundant NSD pressure cartridge in each propulsion system into a second-stage bolt and ignite the BSMs to effect a clean configuration 0.8 second from sequence separation. initialization, which ensures the thrust of each SRB is less than 100,000 pounds. Orbiter yaw Redesigned BSMs flew for the first time in both attitude is held for four seconds and SRB thrust forward and aft locations on STS-125. As a drops to less than 60,000 pounds. The SRBs result of vendor viability and manifest support separate from the ET within 30 milliseconds of issues, space shuttle BSMs are now being the ordnance firing command. manufactured by ATK. The igniter has been redesigned and other changes include material The forward attachment point consists of a ball upgrades driven by obsolescence issues and on the SRB and socket on the ET, held together improvements to process and inspection by one bolt. The bolt contains one NSD techniques. pressure cartridge at each end. The forward attachment point also carries the range safety SRB Cameras system cross-strap wiring connecting each SRB range safety systemr (RSS), and the ET RSS Each SRB flies with a complement of four with each other. cameras, three mounted for exterior views

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during launch, separation and descent; and one The camera videos are available for engineering mounted internal to the forward dome for main review approximately 24 hours following the parachute performance assessment during arrival of the boosters at KSC. descent. Range Safety Systems The ET observation camera is mounted on the The range safety system (RSS) consists of SRB forward skirt and provides a wide-angle two antenna couplers; command receivers/ view of the ET intertank area. The camera is decoders; a dual distributor; a safe and arm activated at lift off by a G-switch and records device with two NSDs; two confined for 350 seconds, after which the recorder is detonating fuse manifolds; seven confined switched to a similar camera in the forward detonator fuse (CDF) assemblies; and one skirt dome to view the deployment and linear-shaped charge. performance of the main parachutes to splash down. These cameras share a digital tape The RSS provides for destruction of a rocket or recorder located within the data acquisition part of it with on-board explosives by remote system. command if the rocket is out of control, to limit danger to people on the ground from The ET ring camera is mounted on the ET crashing pieces, explosions, fire, and poisonous attach ring and provides a view up the stacked substances. vehicle on the orbiter underside and the bipod strut attach point. The space shuttle has two RSSs, one in each SRB. Both are capable of receiving two The forward skirt camera is mounted on the command messages – arm and fire – which are external surface of the SRB forward skirt and transmitted from the ground station. The RSS provides a view aft down the stacked vehicle of is only used when the space shuttle violates a the orbiter underside and the wing leading launch trajectory red line. edge reinforced carbon-carbon (RCC) panels. The antenna couplers provide the proper The ET attach ring camera and forward skirt impedance for radio frequency and ground camera are activated by a global positioning support equipment commands. The command system command at approximately T - 1 minute receivers are tuned to RSS command 56 seconds to begin recording at frequencies and provide the input signal to the approximately T - 50 seconds. The camera distributors when an RSS command is sent. images are recorded through splash down. The command decoders use a code plug to These cameras each have a dedicated recorder prevent any command signal other than the and are recorded in a digital format. The proper command signal from getting into the cameras were designed, qualified, and distributors. The distributors contain the logic implemented by USA after Columbia to to supply valid destruct commands to the RSS provide enhanced imagery capabilities to pyrotechnics. capture potential debris liberation beginning with main engine start and continuing through The NASA standard detonators (NSDs) provide SRB separation. the spark to ignite the CDF that in turn ignites the linear-shaped charge for space shuttle

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destruction. The safe and arm device provides deployment to 52 mph at splashdown, allowing mechanical isolation between the NSDs and the for the recovery and reuse of the boosters. CDF before launch and during the SRB separation sequence. Two 176-foot recovery ships, Freedom Star and Liberty Star, are on station at the splashdown The first message, called arm, allows the zone to retrieve the frustums with drogue onboard logic to enable a destruct and parachutes attached, the main parachutes and illuminates a light on the flight deck display the SRBs. The SRB nose caps and solid rocket and control panel at the commander and pilot motor nozzle extensions are not recovered. The station. The second message transmitted is the SRBs are dewatered using an enhanced diver fire command. The SRB distributors in the operating plug to facilitate tow back. These SRBs are cross-strapped together. Thus, if one plugs are inserted into the motor nozzle and SRB received an arm or destruct signal, the air is pumped into the booster, causing it to signal would also be sent to the other SRB. lay flat in the water to allow it to be easily towed. The boosters are then towed back to Electrical power from the RSS battery in each the refurbishment facilities. Each booster is SRB is routed to RSS system A. The recovery removed from the water and components are battery in each SRB is used to power RSS disassembled and washed with fresh and system B as well as the recovery system in the deionized water to limit saltwater corrosion. SRB. The SRB RSS is powered down during the The motor segments, igniter and nozzle are separation sequence, and the SRB recovery shipped back to ATK in Utah for system is powered up. refurbishment. The nonmotor components and Descent and Recovery structures are disassembled by USA and are refurbished to like-new condition at both KSC After separation and at specified altitudes, the and equipment manufacturers across the SRB forward avionics system initiates the country. release of the nose cap, which houses a pilot parachute and drogue parachute; and the SPACE SHUTTLE SUPER LIGHT WEIGHT frustum, which houses the three main TANK parachutes. Jettison of the nose cap at 15,700 feet deploys a small pilot parachute and The super lightweight external tank (SLWT) begins to slow the SRB decent. At an altitude made its first shuttle flight June 2, 1998, on of 15,200 feet the pilot parachute pulls the mission STS-91. The SLWT is 7,500 pounds drogue parachute from the frustum. The lighter than the standard external tank. The drogue parachute fully inflates in stages, and at lighter weight tank allows the shuttle to deliver 5,500 feet pulls the frustum away from the SRB, International Space Station elements (such as which initiates the deployment of the three the service module) into the proper orbit. main parachutes. The parachutes also inflate in The SLWT is the same size as the previous stages and further slow the decent of the SRBs design. But the liquid hydrogen tank and the to their final velocity at splashdown. The liquid oxygen tank are made of aluminum parachutes slow each SRB from 368 mph at first lithium, a lighter, stronger material than the metal alloy used for the shuttle’s current tank.

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The tank’s structural design has also been propellant used, the tank is jettisoned and falls improved, making it 30 percent stronger and in a preplanned trajectory. Most of the tank 5 percent less dense. disintegrates in the atmosphere, and the remainder falls into the ocean. The SLWT, like the standard tank, is manufactured at NASA’s Michoud Assembly The external tank is manufactured at NASA’s Facility, near New Orleans, by Lockheed Michoud Assembly Facility in New Orleans by Martin. Lockheed Martin Space Systems.

The 154-foot-long external tank is the largest Foam Facts single component of the space shuttle. It stands taller than a 15-story building and has a The external tank is covered with spray-on diameter of about 27 feet. The external tank foam insulation that insulates the tank before holds over 530,000 gallons of liquid hydrogen and during launch. More than 90 percent of the and liquid oxygen in two separate tanks. The tank’s foam is applied using an automated hydrogen (fuel) and liquid oxygen (oxidizer) system, leaving less than 10 percent to be are used as propellants for the shuttle’s three applied manually. main engines. There are two types of foam on the external EXTERNAL TANK tank, known as the Thermal Protection System (TPS). One is low-density, closed-cell foam on The 154-foot-long external tank is the largest the tank acreage and is known as Spray-On- single component of the space shuttle. It stands Foam-Insulation, often referred to by its taller than a 15-story building and has a acronym, SOFI. Most of the tank is covered by diameter of about 27 feet. The external tank either an automated or manually applied SOFI. holds more than 530,000 gallons of liquid Most areas around protuberances, such as hydrogen and liquid oxygen in two separate brackets and structural elements, are applied by tanks, the forward liquid oxygen tank and the pouring foam ingredients into part-specific aft liquid hydrogen tank. An unpressurized molds. The other, called ablator, is a denser intertank unites the two propellant tanks. composite material made of silicone resins and cork. An ablator is a material that dissipates Liquid hydrogen (fuel) and liquid oxygen heat by eroding. It is used on areas of the (oxidizer) are used as propellants for the external tank subjected to extreme heat, such as shuttle’s three main engines. The external tank the aft dome near the engine exhaust, and weighs 58,500 pounds empty and remaining protuberances, such as the cable 1,668,500 pounds when filled with propellants. trays. These areas are exposed to extreme aerodynamic heating. The external tank is the “backbone” of the shuttle during launch, providing structural Closed-cell foam used on the tank was support for attachment with the solid rocket developed to keep the propellants that fuel the boosters and orbiter. It is the only component shuttle’s three main engines at optimum of the shuttle that is not reused. Approximately temperature. It keeps the shuttle’s liquid 8.5 minutes after reaching orbit, with its hydrogen fuel at -423 degrees Fahrenheit

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and the liquid oxygen tank at near Multiple visual inspections of all foam surfaces -297 degrees Fahrenheit, even as the tank sits are performed after the spraying is complete. under the hot Florida sun. At the same time, the foam prevents a buildup of ice on the Most of the foam is applied at NASA’s outside of the tank. Michoud Assembly Facility in New Orleans when the tank is manufactured, including most The foam insulation must be durable enough to of the “closeout” areas, or final areas applied. endure a 180-day stay at the launch pad, These closeouts are done either by hand withstand temperatures up to 115 degrees pouring or manual spraying. Additional Fahrenheit, humidity as high as 100 percent, closeouts are completed once the tank reaches and resist sand, salt, fog, rain, solar radiation NASA’s Kennedy Space Center, Fla. and even fungus. Then, during launch, the foam must tolerate temperatures as high as The SLWT made its first shuttle flight in June 2,200 degrees Fahrenheit generated by 1998 on mission STS-91. The SLWT is 7,500 aerodynamic friction and radiant heating from pounds lighter than previously flown tanks. the 3,000 degrees Fahrenheit main engine The SLWT is the same size as the previous plumes. Finally, when the external tank begins design, but the liquid hydrogen tank and the reentry into the Earth’s atmosphere about liquid oxygen tank are made of aluminum 30 minutes after launch, the foam maintains the lithium, a lighter, stronger material than the tank’s structural temperatures and allows it to metal alloy used previously. safely disintegrate over a remote ocean location. Beginning with the first Return to Flight Though the foam insulation on the majority of mission, STS-114 in June 2005, several the tank is only 1-inch thick, it adds improvements were made to improve safety 4,823 pounds to the tank’s weight. In the areas and flight reliability. of the tank subjected to the highest heating, Forward Bipod insulation is somewhat thicker, between 1.5 to 3 inches thick. Though the foam’s density The external tank’s forward shuttle attach varies with the type, an average density is fitting, called the bipod, was redesigned to about 2.4 pounds per cubic foot. eliminate the large insulating foam ramps as a source of debris. Each external tank has two Application of the foam, whether automated by bipod fittings that connect the tank to the computer or hand-sprayed, is designed to meet orbiter through the shuttle’s two forward NASA’s requirements for finish, thickness, attachment struts. Four rod heaters were roughness, density, strength and adhesion. As placed below each forward bipod, replacing the in most assembly production situations, the large insulated foam protuberance airload foam is applied in specially designed, (PAL) ramps. environmentally controlled spray cells and applied in several phases, often over a period of Liquid Hydrogen Tank & Liquid Oxygen several weeks. Before spraying, the foam’s raw Intertank Flange Closeouts material and mechanical properties are tested to ensure they meet NASA specifications. The liquid hydrogen tank flange located at the bottom of the intertank and the liquid oxygen

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tank flange located at the top of the intertank and cable tray brackets, where these PAL ramps provide joining mechanisms with the intertank. were removed to make the geometry of the After each of these three component tanks, ramps consistent with other locations on liquid oxygen, intertank and liquid hydrogen, the tank and thereby provide consistent are joined mechanically, the flanges at both aerodynamic flow. Nine extensions were ends are insulated with foam. An enhanced added, six on the liquid hydrogen tank and closeout, or finishing, procedure was added to three on the liquid oxygen tank. improve foam application to the stringer, or intertank ribbing, and to the upper and lower Engine Cutoff Sensor Modification area of both the liquid hydrogen and liquid Beginning with STS-122, ET-125, which oxygen intertank flanges. launched on Feb. 7, 2008, the engine cutoff Liquid Oxygen Feedline Bellows (ECO) sensor system feed-through connector on the liquid hydrogen tank was modified by The liquid oxygen feedline bellows were soldering the connector’s pins and sockets to reshaped to include a “drip lip” that allows address false readings in the system. All condensate moisture to run off and prevent subsequent tanks after ET-125 have the same freezing. A strip heater was added to the modification. forward bellow to further reduce the potential of high density ice or frost formation. Joints on Liquid Hydrogen Tank Ice Frost Ramps the liquid oxygen feedline assembly allow the ET-128, which flew on the STS-124 shuttle feedline to move during installation and during mission, May 31, 2008, was the first tank to fly liquid hydrogen tank fill. Because it must flex, with redesigned liquid hydrogen tank ice frost it cannot be insulated with foam like the ramps. Design changes were incorporated at remainder of the tank. all 17 ice frost ramp locations on the liquid Other tank improvements include: hydrogen tank, stations 1151 through 2057, to reduce foam loss. Although the redesigned Liquid Oxygen & Liquid Hydrogen ramps appear identical to the previous design, Protuberance Airload (PAL) Ramps several changes were made. PDL* and NCFI foam have been replaced with BX* manual External tank ET-119, which flew on the second spray foam in the ramp’s base cutout to reduce Return to Flight mission, STS-121, in July 2006, debonding and cracking; Pressline and cable was the first tank to fly without PAL ramps tray bracket feet corners have been rounded to along portions of the liquid oxygen and reduce stresses; shear pin holes have been liquid hydrogen tanks. These PAL ramps were sealed to reduce leak paths; isolators were extensively studied and determined to not be primed to promote adhesion; isolator corners necessary for their original purpose, which was were rounded to help reduce thermal to protect cable trays from aeroelastic instability protection system foam stresses; BX manual during ascent. Extensive tests were conducted spray was applied in bracket pockets to reduce to verify the shuttle could fly safely without geometric voids. these particular PAL ramps. Extensions were added to the ice frost ramps for the pressline

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*BX is a type of foam used on the tank’s Titanium brackets, much less thermally “closeout,” or final finished areas; it is applied conductive than aluminum, replaced aluminum manually or hand-sprayed. PDL is an acronym brackets at four locations, XT 1129, XT 1377, for product development laboratory, the first Xt 1624 and Xt 1871. This change minimizes ice supplier of the foam during the early days of formation in under-insulated areas, and the external tank’s development. PDL is reduces the amount of foam required to cover applied by pouring foam ingredients into a the brackets and the propensity for ice mold. NCFI foam is used on the aft dome, or development. Zero-gap/slip plane Teflon bottom, of the liquid hydrogen tank. material was added to the upper outboard monoball attachment to eliminate ice adhesion. Liquid Oxygen Feedline Brackets Additional foam has been added to the liquid ET-128 also was the first tank to fly with oxygen feedline to further minimize ice redesigned liquid oxygen feedline brackets. formation along the length of the feedline.

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LAUNCH AND LANDING

LAUNCH RETURN TO LAUNCH SITE

As with all previous space shuttle launches, If one or more engines shut down early and Discovery has several options to abort its there is not enough energy to reach Zaragoza or ascent, if needed, after engine failures or other another TAL site, the shuttle would pitch systems problems. Shuttle launch abort around back toward the Kennedy Space Center philosophy is intended to facilitate safe (KSC) until within gliding distance of the recovery of the flight crew and intact recovery shuttle landing facility. For the launch to of the orbiter and its payload. proceed, weather conditions must be forecast to be acceptable for a possible landing at KSC Abort modes include about 20 minutes after liftoff. ABORT TO ORBIT ABORT ONCE AROUND

This mode is used if there is a partial loss of An abort once around is selected if the vehicle main engine thrust late enough to permit cannot achieve a viable orbit or will not have reaching a minimal 105 by 85 nautical mile orbit enough propellant to perform a deorbit burn, with the orbital maneuvering system engines. but has enough energy to circle the Earth once The engines boost the shuttle to a safe orbital and land about 90 minutes after liftoff. The altitude when it is impossible to reach the KSC shuttle landing facility is the primary planned orbital altitude. landing site for an AOA, and White Sands TRANSOCEANIC ABORT LANDING Space Harbor, N.M., is the backup site.

The loss of one or more main engines midway LANDING through powered flight would force a landing The primary landing site for Discovery on at either Zaragoza, Spain; Morón, Spain; or STS-133 is Kennedy’s Shuttle Landing Facility. Istres, France. For the launch to proceed, Alternate landing sites that could be used if weather conditions must be acceptable at one of needed because of weather conditions or these transoceanic abort landing (TAL) sites. systems failures are at Edwards Air Force Base, Calif., and White Sands Space Harbor, N.M.

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ACRONYMS AND ABBREVIATIONS

A/G Alignment Guides A/L Airlock AAA Avionics Air Assembly ABC Audio Bus Controller ACBM Active Common Berthing Mechanism ACDU Airlock Control and Display Unit ACO Assembly Checkout Officer ACS Atmosphere Control and Supply ACU Arm Control Unit ADS Audio Distribution System AE Approach Ellipsoid AEP Airlock Electronics Package AHMS Advanced Health Management System AI Approach Initiation AIS Automatic Identification System AJIS Alpha Joint Interface Structure AM Atmosphere Monitoring AMOS Air Force Maui Optical and Supercomputing Site AOA Abort Once Around AOH Assembly Operations Handbook APAS Androgynous Peripheral Attachment APCU Assembly Power Converter Unit APE Antenna Pointing Electronics Audio Pointing Equipment APFR Articulating Portable Foot Restraint APM Antenna Pointing Mechanism APS Automated Payload Switch APV Automated Procedure Viewer AR Atmosphere Revitalization ARCU American-to-Russian Converter Unit ARS Atmosphere Revitalization System ASW Application Software ATA Ammonia Tank Assembly ATCS Active Thermal Control System ATO Abort To Orbit ATU Audio Terminal Unit

BAD Broadcast Ancillary Data BC Bus Controller

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BCDU Battery Charge/Discharge Unit Berthing Mechanism Control and Display Unit BEP Berthing Mechanism Electronics Package BGA Beta Gimbal Assembly BIC Bus Interface Controller BIT Built-In Test BLT Boundary Layer Transition BM Berthing Mechanism BOS BIC Operations Software BSM Booster Separation Motors BSS Basic Software BSTS Basic Standard Support Software BXF Boiling Experiment Facility

C&C Command and Control C&DH Command and Data Handling C&T Communication and Tracking C&W Caution and Warning C/L Crew Lock C/O Checkout CAM Collision Avoidance Maneuver CAPE Canister for All Payload Ejections CAS Common Attach System CB Control Bus CBCS Centerline Berthing Camera System CBM Common Berthing Mechanism CCA Circuit Card Assembly CCAA Common Cabin Air Assembly CCHA Crew Communication Headset Assembly CCP Camera Control Panel CCT Communication Configuration Table CCTV Closed-Circuit Television CDF Confirmed Detonator CDR Space Shuttle Commander CDRA Carbon Dioxide Removal Assembly CETA Crew Equipment Translation Aid CHeCS Crew Health Care System CHX Cabin Heat Exchanger CISC Complicated Instruction Set Computer CLA Camera Light Assembly CLPA Camera Light Pan Tilt Assembly CMG Control Moment Gyro

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COTS Commercial Off the Shelf Commercial Orbital Transportation Service CP3 Camera Port 3 CPA Control Panel Assembly CPB Camera Power Box CR Change Request CRT Cathode-Ray Tube CSA Canadian Space Agency CSA-CP Compound Specific Analyzer CSLM-2 Coarsening in Solid Liquid Mixtures-2 CTC Cargo Transport Container CVIU Common Video Interface Unit CVT Current Value Table CZ Communication Zone

DB Data Book DC Docking Compartment DCSU Direct Current Switching Unit DDCU DC-to-DC Converter Unit DEM Demodulator DFL Decommutation Format Load DIU Data Interface Unit DMS Data Management System DMS-R Data Management System-Russian DPG Differential Pressure Gauge DPU Baseband Data Processing Unit DRTS Japanese Data Relay Satellite DYF Display Frame

E/L Equipment Lock EATCS External Active Thermal Control System EBCS External Berthing Camera System ECC Error Correction Code ECLS Environmental Controls and Life Support ECLSS Environmental Control and Life Support System ECS Environmental Control System ECU Electronic Control Unit EDSU External Data Storage Unit EDU EEU Driver Unit EE End Effector EETCS Early External Thermal Control System EEU Experiment Exchange Unit

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EF Exposed Facility EFBM Exposed Facility Berthing Mechanism EFHX Exposed Facility Heat Exchanger EFU Exposed Facility Unit EGIL Electrical, General Instrumentation, and Lighting EIU Ethernet Interface Unit ELC ExPRESS Logistics Carrier ELITE-S2 Elaboratore Immagini Televisive – Space 2 ELM-ES Japanese Experiment Logistics Module – Exposed Section ELM-PS Japanese Experiment Logistics Module – Pressurized Section ELPS Emergency Lighting Power Supply EMGF Electric Mechanical Grapple Fixture EMI Electro-Magnetic Imaging EMU Extravehicular Mobility Unit E-ORU EVA Essential ORU EP Exposed Pallet EPS Electrical Power System ES Exposed Section ESA European Space Agency ESC JEF System Controller ESP2 External Storage Platform 2 ESW Extended Support Software ET External Tank ETCS External Thermal Control System ETI Elapsed Time Indicator ETRS EVA Temporary Rail Stop ETVCG External Television Camera Group EV Extravehicular EVA Extravehicular Activity EXP-D Experiment-D Express Ecpedite the Processing of Experiments to Space Station EXT External

FA Fluid Accumulator FAS Flight Application Software FCT Flight Control Team FD Flight Day FDDI Fiber Distributed Data Interface FDIR Fault Detection, Isolation, and Recovery FDS Fire Detection System FE Flight Engineer FET-SW Field Effect Transistor Switch

84 ACRONYMS/ABBREVIATIONS NOVEMBER 2010

FGB Functional Cargo Block FOR Frame of Reference FPMU Floating Potential Measurement Unit FPP Fluid Pump Package FR Flight Rule FRD Flight Requirements Document FRGF Flight Releasable Grapple Fixture FRM Functional Redundancy Mode FSE Flight Support Equipment FSEGF Flight Support Equipment Grapple Fixture FSM Fuel Supply Module FSW Flight Software FTT Functional Task Test

GAS Get-Away Special GATOR Grappling Adaptor to On-orbit Railing GCA Ground Control Assist GLA General Lighting Assemblies General Luminaire Assembly GLONASS Global Navigational Satellite System GM General Motors GNC Guidance, Navigation, and Control GPC General Purpose Computer GPS Global Positioning System GPSR Global Positioning System Receiver GUI Graphical User Interface

H&S Health and Status HCE Heater Control Equipment HCTL Heater Controller HD High Definition HEPA High Efficiency Particulate Acquisition HPA High Power Amplifier HPGT High Pressure Gas Tank HPP Hard Point Plates HPU Hydraulic Power Unit HRDR High Rate Data Recorder HREL Hold/Release Electronics HRFM High Rate Frame Multiplexer HRM Hold Release Mechanism HRMS High Rate Multiplexer and Switcher HRS Heat Rejection Subsystem

NOVEMBER 2010 ACRONYMS/ABBREVIATIONS 85

HTV H-II Transfer Vehicle HTVCC HTV Control Center HTV Prox HTV Proximity HX Heat Exchanger

I/F Interface IAA Intravehicular Antenna Assembly IAC Internal Audio Controller IBM International Business Machines ICB Inner Capture Box ICC Integrated Cargo Carrier ICS Interorbit Communication System ICS-EF Interorbit Communication System - Exposed Facility IDRD Increment Definition and Requirements Document IELK Individual Equipment Liner Kit IFHX Interface Heat Exchanger IMCS Integrated Mission Control System IMCU Image Compressor Unit IMV Intermodule Ventilation INCO Instrumentation and Communication Officer IP International Partner IP-PCDU ICS-PM Power Control and Distribution Unit IP-PDB Payload Power Distribution Box ISP International Standard Payload ISPR International Standard Payload Rack ISS International Space Station ISSSH International Space Station Systems Handbook ITCS Internal Thermal Control System ITS Integrated Truss Segment IV Intravehicular IVA Intravehicular Activity IVSU Internal Video Switch Unit IWIS ISS Wireless Instrumentation System

JAXA Japan Aerospace Exploration Agency JCP JEM Control Processor JEF JEM Exposed Facility JEM Japanese Experiment Module JEMAL JEM Airlock JEM-EF Japanese Experiment Module Exposed Facility JEM-PM Japanese Experiment Module – Pressurized Module JEMRMS Japanese Experiment Module Remote Manipulator System

86 ACRONYMS/ABBREVIATIONS NOVEMBER 2010

JEUS Joint Expedited Undocking and Separation JFCT Japanese Flight Control Team JLE Japanese Experiment Logistics Module – Exposed Section JLP Japanese Experiment Logistics Module – Pressurized Section JLP-EDU JLP-EFU Driver Unit JLP-EFU JLP Exposed Facility Unit JPM Japanese Pressurized Module JPM WS JEM Pressurized Module Workstation JSC Johnson Space Center JTVE JEM Television Equipment

Kbps Kilobit per second KOS Keep Out Sphere KSC Kennedy Space Center

LB Local Bus LCA LAB Cradle Assembly LCD Liquid Crystal Display LED Light Emitting Diode LEE Latching End Effector LIDAR Light Intensification Detection and Ranging LMC Lightweight MPESS Carrier LSW Light Switch LTA Launch-to-Activation LTAB Launch-to-Activation Box LTL Low Temperature Loop

MA Main Arm MAUI Main Analysis of Upper-Atmospheric Injections Mb Megabit Mbps Megabit per second MBS Mobile Base System MBSU Main Bus Switching Unit MCA Major Constituent Analyzer MCC Mission Control Center MCC-H Mission Control Center – Houston MCC-M Mission Control Center – Moscow MCDS Multifunction Cathode-Ray Tube Display System MCS Mission Control System MDA MacDonald, Dettwiler and Associates Ltd. MDM Multiplexer/Demultiplexer MDP Management Data Processor MEC Master Event Controller

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MECO Main Engine Cut Off MELFI Minus Eighty-Degree Laboratory Freezer for station MGB Middle Grapple Box MIP Mission Integration Plan MISSE Materials International Space Station Experiment MKAM Minimum Keep Alive Monitor MLE Middeck Locker Equivalent MLI Multi-layer Insulation MLM Multipurpose Laboratory Module MLP Mobile Launcher Platform MMOD Micrometeoroid/Orbital Debris MOD Modulator MON Television Monitor MPC Main Processing Controller MPESS Multipurpose Experiment Support Structure MPEV Manual Pressure Equalization Valve MPL Manipulator Retention Latch MPLM Multipurpose Logistics Module MPM Manipulator Positioning Mechanism MPV Manual Procedure Viewer MRM Mini-Research Module MSD Mass Storage Device MSFC Marshall Space Flight Center MSP Maintenance Switch Panel MSS Mobile Servicing System MT Mobile Tracker Mobile Transporter MTL Moderate Temperature Loop MUX Data Multiplexer

NASA National Aeronautics and Space Administration NCS Node Control Software NET No Earlier Than NLP National Lab Pathfinder NLT No Less Than n.mi. nautical mile NPRV Negative Pressure Relief Valve NSV Network Service NTA Nitrogen Tank Assembly NTSC National Television Standard Committee

88 ACRONYMS/ABBREVIATIONS NOVEMBER 2010

OBSS Orbiter Boom Sensor System OCA Orbital Communications Adapter OCAD Operational Control Agreement Document OCAS Operator Commanded Automatic Sequence ODF Operations Data File ODS Orbiter Docking System OI Orbiter Interface OIU Orbiter Interface Unit OMS Orbital Maneuvering System OODT Onboard Operation Data Table ORCA Oxygen Recharge Compressor Assembly ORU Orbital Replacement Unit OS Operating System OSA Orbiter-based Station Avionics OSE Orbital Support Equipment OTCM ORU and Tool Changeout Mechanism OTP ORU and Tool Platform

P/L Payload PAL Protuberance Airload PAM Payload Attach Mechanism PAO Public Affairs Office PAS Payload Adapter System PBA Portable Breathing Apparatus PCA Pressure Control Assembly PCBM Passive Common Berthing Mechanism PCN Page Change Notice PCS Portable Computer System PCU Power Control Unit Plasma Contactor Unit PDA Payload Disconnect Assembly PDB Power Distribution Box PDGF Power and Data Grapple Fixture PDH Payload Data Handling unit PDL Product Development Laboratory PDRS Payload Deployment Retrieval System PDU Power Distribution Unit PEC Passive Experiment Container PEHG Payload Ethernet Hub Gateway PFE Portable Fire Extinguisher PFRAM Passive Flight Releasable Attachment Mechanism PGSC Payload General Support Computer

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PIB Power Interface Box PIC Pyrotechnic Initiation Controller PIU Payload Interface Unit PLB Payload Bay PLBD Payload Bay Door PLC Pressurized Logistics Carrier PLT Payload Laptop Terminal Space Shuttle Pilot PM Pressurized Module Pump Module PMA Pressurized Mating Adapter PMCU Power Management Control Unit PMM Pressurized Multipurpose Module PMU Pressurized Mating Adapter POA Payload Orbital Replacement Unit (ORU) Accommodation POR Point of Resolution PPA Pump Package Assembly PPRV Positive Pressure Relief Valve PRCS Primary Reaction Control System PREX Procedure Executor PRLA Payload Retention Latch Assembly PRO Payload Rack Officer PROX Proximity Communications Center psia Pounds per Square Inch Absolute PSP Payload Signal Processor PSRR Pressurized Section Resupply Rack PTCS Passive Thermal Control System PTR Port Thermal Radiator PTU Pan/Tilt Unit PVCU Photovoltaic Controller Unit PVM Photovoltaic Module PVR Photovoltaic Radiator PVTCS Photovoltaic Thermal Control System

QD Quick Disconnect

R&MA Restraint and Mobility Aid RACU Russian-to-American Converter Unit RAM Read Access Memory RAMBO-2 Ram Burn Observation-2 RBVM Radiator Beam Valve Module RCC Range Control Center

90 ACRONYMS/ABBREVIATIONS NOVEMBER 2010

RCS Reaction Control System RCT Rack Configuration Table RF Radio Frequency RGA Rate Gyro Assemblies RHC Rotational Hand Controller RIGEX Rigidizable Inflatable Get-Away Special Experiment RIP Remote Interface Panel RLF Robotic Language File RLT Robotic Laptop Terminal RMS Remote Manipulator System ROEU Remotely Operated Electrical Umbilical ROM Read Only Memory R-ORU Robotics Compatible Orbital Replacement Unit ROS Russian Orbital Segment RPC Remote Power Controller RPCM Remote Power Controller Module RPDA Remote Power Distribution Assembly RPM Roll Pitch Maneuver RS Russian Segment RSP Return Stowage Platform RSR Resupply Stowage Rack RSS Range Safety System RT Remote Terminal R2 Robonaut 2 RTAS Rocketdyne Truss Attachment System RTLS Return To Launch Site RVFS Rendezvous Flight Software RWS Robotics Workstation

S Starboard SAFER Simplified Aid for EVA Rescue SAM SFA Airlock Attachment Mechanism SAME Smoke and Aerosol Measurement Experiment SAPA Small Adapter Plate Assembly SARJ Solar Alpha Rotary Joint SASA S-Band Antenna Sub-Assembly SCU Sync and Control Unit SD Smoke Detector SDS Sample Distribution System SEDA Space Environment Data Acquisition equipment SEDA-AP Space Environment Data Acquisition equipment - Attached Payload SEITE Shuttle Exhaust Ion Turbulence Experiments

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SELS SpaceOps Electronic Library System SEU Single Event Upset SFA Small Fine Arm SFAE SFA Electronics SI Smoke Indicator SIMPLEX Shuttle Ionospheric Modification with Pulsed Local EXhaust SLM Structural Latch Mechanism SLP-D Spacelab Pallet – D SLP-D1 Spacelab Pallet – Deployable SLP-D2 Spacelab Pallet - D2 SLT Station Laptop Terminal System Laptop Terminal SLWT Super Light Weight Tank SM Service Module SMDP Service Module Debris Panel SOC System Operation Control SODF Space Operations Data File SPA Small Payload Attachment SPB Survival Power Distribution Box SPDA Secondary Power Distribution Assembly SPDM Special Purpose Dexterous Manipulator SPEC Specialist SRAM static RAM SRB Solid Rocket Booster SRMS Shuttle Remote Manipulator System SSAS Segment-to-Segment Attach System SSC Station Support Computer SSCB Space Station Control Board SSE Small Fine Arm Storage Equipment SSIPC Space Station Integration and Promotion Center SSME Space Shuttle Main Engine SSOR Space-to-Space Orbiter Radio SSP Standard Switch Panel SSPTS Station-to-Shuttle Power Transfer System SSRMS Space Station Remote Manipulator System STC Small Fire Arm Transportation Container STR Starboard Thermal Radiator STS Space Transfer System STVC SFA Television Camera SVS Space Vision System

92 ACRONYMS/ABBREVIATIONS NOVEMBER 2010

T Thrust TA Thruster Assist TAC TCS Assembly Controller TAC-M TCS Assembly Controller - M TAL Transoceanic Abort Landing TCA Thermal Control System Assembly TCB Total Capture Box TCCS Trace Contaminant Control System TCCV Temperature Control and Check Valve TCS Thermal Control System Trajectory Control Sensor TCV Temperature Control Valve TDK Transportation Device Kit TDRS Tracking and Data Relay Satellite THA Tool Holder Assembly THC Temperature and Humidity Control Translational Hand Controller THCU Temperature and Humidity Control Unit TIU Thermal Interface Unit TKSC Tsukuba Space Center (Japan) TLM Telemetry TMA Russian vehicle designation TMR Triple Modular Redundancy TPL Transfer Priority List TRRJ Thermal Radiator Rotary Joint TUS Trailing Umbilical System TVC Thrust Vector Control

UCCAS Unpressurized Cargo Carrier Attach System UCM Umbilical Connect Mechanism UCM-E UCM – Exposed Section Half UCM-P UCM – Payload Half UHF Ultrahigh Frequency UIL User Interface Language ULC Unpressurized Logistics Carrier UMA Umbilical Mating Adapter UOP Utility Outlet Panel UPC Up Converter USA United Space Alliance US LAB United States Laboratory USOS United States On-Orbit Segment UTA Utility Transfer Assembly

NOVEMBER 2010 ACRONYMS/ABBREVIATIONS 93

VAJ Vacuum Access Jumper VBSP Video Baseband Signal Processor VCU Video Control Unit VDS Video Distribution System VLU Video Light Unit VRA Vent Relief Assembly VRCS Vernier Reaction Control System VRCV Vent Relief Control Valve VRIV Vent Relief Isolation Valve VSU Video Switcher Unit VSW Video Switcher

WAICO Waiving and Coiling WCL Water Cooling Loop WETA Wireless Video System External Transceiver Assembly WIF Work Interface WPA Water Processor Assembly WRM Water Recovery and Management WRS Water Recovery System WS Water Separator Work Site Work Station WVA Water Vent Assembly

ZSR Zero-g Stowage Rack

94 ACRONYMS/ABBREVIATIONS NOVEMBER 2010

MEDIA ASSISTANCE

NASA TELEVISION AND INTERNET of space satellites, as well as media briefings, presentations by expert lecturers, astronaut The digital NASA Television system provides interviews and other special events, all in the higher quality images and better use of satellite improved detail and clarity of HD. bandwidth, meaning multiple channels from multiple NASA program sources at the same Getting NASA TV via satellite (AMC3 time. Transponder 15C)

Digital NASA TV has the following four digital In continental North America, Alaska and channels: Hawaii, NASA Television’s Public, Education, Media and HD channels are MPEG-2 digital 1. NASA Public Service (“Free to Air”), C-band signals carried by QPSK/DVB-S featuring documentaries, archival modulation on satellite AMC-3, transponder programming, and coverage of NASA 15C, at 87 degrees west longitude. Downlink missions and events. frequency is 4000 MHz, horizontal polarization, 2. NASA Education Services (“Free to with a data rate of 38.86 Mhz, symbol rate of Air/Addressable”), dedicated to providing 28.1115 Ms/s, and 3/4 FEC. A Digital Video educational programming to schools, Broadcast (DVB) compliant Integrated Receiver educational institutions and museums. Decoder (IRD) is needed for reception. Effective Sept. 1, 2010, NASA TV changed the 3. NASA Media Services (“Addressable”), for primary audio configuration for each of its four broadcast news organizations. channels to AC-3, making each channel’s 4. NASA Mission Operations (Internal Only). secondary audio MPEG 1 Layer II. For NASA TV downlink information, schedules Digital NASA TV channels may not always and links to streaming video, visit have programming on every channel http://www.nasa.gov/ntv simultaneously. Television Schedule NASA Television Now in High Definition A schedule of key mission events and media NASA TV now has a full-time High Definition briefings during the mission will be detailed in (HD) Channel available at no cost to cable and a NASA TV schedule posted at the link above. satellite service providers. Live coverage of The schedule will be updated as necessary and space shuttle missions; on-orbit video of Earth will also be available at captured by astronauts aboard the International http://www.nasa.gov/multimedia/nasatv/missi Space Station; and rocket launches of advanced on_schedule.html scientific spacecraft are among the programming offered on NASA HD. Also available are imagery from NASA’s vast array

NOVEMBER 2010 MEDIA ASSISTANCE 95

Status Reports Information on the International Space Station is available at: http://www.nasa.gov/station Status reports and timely updates on launch countdown, mission progress, and landing The NASA Human Space Flight Web contains operations will be posted at: an up-to-date archive of mission imagery, video http://www.nasa.gov/shuttle and audio at: http://spaceflight.nasa.gov

Internet Information Information on safety enhancements for the 2005 Return to Flight effort is available at: Information on NASA and its programs is http://www.nasa.gov/returntoflight/system/in available through the NASA Home Page and dex.html the NASA Public Affairs Home Page: http://www.nasa.gov Resources for educators can be found at: or http://education.nasa.gov http://www.nasa.gov/newsinfo/index.html

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PUBLIC AFFAIRS CONTACTS

NASA HEADQUARTERS Kylie Clem WASHINGTON Newsroom Manager 281-483-5111 John Yembrick [email protected] International Partners and Shuttle, Space Station Policy Kyle Herring 202-358-1100 Space Shuttle Program [email protected] 281-483-5111 [email protected] Michael Curie Shuttle, Space Station Policy Rob Navias 202-358-1100 Mission Operations Lead [email protected] 281-483-5111 [email protected] Stephanie Schierholz Shuttle, Space Station Policy Kelly Humphries 202-358-1100 International Space Station Program and [email protected] Mission Operations Directorate 281-483-5111 Joshua Buck [email protected] Shuttle, Space Station Policy 202-358-1100 Nicole Cloutier-Lemasters [email protected] Astronauts 281-483-5111 Michael Braukus [email protected] Research in Space 202-358-1979 Josh Byerly [email protected] Advanced Planning and Mission Operations 281-483-5111 JOHNSON SPACE CENTER [email protected] HOUSTON Bill Jeffs James Hartsfield Space Life Sciences Chief, Mission and Media Support 281-483-5111 281-483-5111 [email protected] [email protected]

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KENNEDY SPACE CENTER STENNIS SPACE CENTER CAPE CANAVERAL, FLA. BAY ST. LOUIS, MISS.

Allard Beutel Rebecca Strecker News Chief News Chief 321-867-2468 228-688-3249 [email protected] [email protected]

Candrea Thomas Paul Foerman Space Shuttle Public Affairs Team Lead 321-867-2468 228-688-1880 [email protected] [email protected]

Tracy Young AMES RESEARCH CENTER International Space Station MOFFETT FIELD, CALIF. 321-867-2468 [email protected] Michael Mewhinney News Chief MARSHALL SPACE FLIGHT CENTER 650-604-3937 HUNTSVILLE, ALA. [email protected]

Dom Amatore Rachel Hoover Public Affairs Office Manager Space Science 256-544-0034 650-604-0643 [email protected] [email protected]

June Malone Ruth Marlaire News Chief Earth Sciences 256-544-0034 650-604-4709 [email protected] [email protected]

Steve Roy Cathy Weselby Space Shuttle Propulsion and Space Station 650-604-2791 Science [email protected] 256-544-0034 [email protected] Karen Jenvey 650-604-4034 Jennifer Stanfield [email protected] Propulsion Systems 256-544-0034 [email protected]

98 PUBLIC AFFAIRS CONTACTS NOVEMBER 2010

DRYDEN FLIGHT RESEARCH CENTER Keith Henry EDWARDS, CALIF. News Chief 757-864-6120 Kevin Rohrer [email protected] Public Affairs Team Lead 661-276-3595 Kathy Barnstorff [email protected] Space Ops 757-864-9886 Alan Brown [email protected] News Chief 661-276-2665 Amy Johnson [email protected] Exploration 757-864-7022 Leslie Williams [email protected] Space Shuttle 661-276-3893 UNITED SPACE ALLIANCE [email protected] Kari Fluegel GLENN RESEARCH CENTER Houston Operations CLEVELAND, OHIO 281-280-6959 281-796-7712 Lori Rachul [email protected] News Chief Tracy Yates 216-433-8806 Florida Operations [email protected] 321-861-3956 Sally Harrington 321-750-1739 (cell) Space Ops [email protected] 216-433-2037 [email protected] BOEING

Katherine Martin Ed Memi Spaceflight Systems, Research and Technology International Space Station/Space Shuttle 216-433-2406 Communications [email protected] The Boeing Co. Space Exploration Division LANGLEY RESEARCH CENTER 281-226-4029 HAMPTON, VA. [email protected]

Marny Skora Communications Director 757-864-6121 [email protected]

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CANADIAN SPACE AGENCY (CSA) JAPAN AEROSPACE EXPLORATION AGENCY (JAXA) Jean-Pierre Arseneault Manager, Media Relations & Information Kumiko Sagara Services JAXA Public Affairs Representative Canadian Space Agency Houston 514-824-0560 (cell) 281-792-7468 [email protected] [email protected]

Media Relations Office JAXA Public Affairs Office Canadian Space Agency Tokyo, Japan 450-926-4370 011-81-50-3362-4374 [email protected] EUROPEAN SPACE AGENCY (ESA) ROSCOSMOS Jean Coisne Head of European Astronaut Centre Outreach Asya Samojlova office Assistant to Alexander Vorobiev, Press Communication Department Secretary to the General Director 49-2203-60-01-110 7-495-975-4458 (Press Office) [email protected] [email protected] or [email protected]

100 PUBLIC AFFAIRS CONTACTS NOVEMBER 2010