National Aeronautics and Space Administration
Space Launch System And NASA’s Path to Mars
Todd May Program Manager Space Launch System (SLS) Program August 2014
www.nasa.gov/sls www.nasa.gov/sls Mars Is The Mission
www.nasa.gov/sls SLS_OPAG.2 Mars: The Human Destination
Mars Landing: Heading for the High Ground Courtesy of Dan Durda
www.nasa.gov/sls SLS_OPAG.3 The Path to Mars
www.nasa.www.nasa.gov/slsgov/sls 8588_Lunch_and_Learn_.4 Mars Is the World’s Mission
www.nasa.gov/sls Revolutionary Evolution
5, 8.4 or 10 Meter Payload Fairings
Orion
Upper Stage Interim Cryogenic Propulsion Stage
Core Stage
Five-Segment Solid Liquid or Solid Rocket Boosters Advanced Boosters
Block I Block II 70 metric tons 4 RS-25 Engines 130 metric tons www.nasa.gov/sls Benefit: High Departure Energy
' Even the Initial configuration of SLS Cargo Flyby
offers orders of magnitude greater 70.00 SLS Block 1 Orion + iCPS payload-to-destination energy SLS Block 1 5.0m Fairing + iCPS 60.00 compared to existing launch vehicles; SLS Block 1B 8.4m Fairing + EUS SLS Block 2B 8.4m Fairing + EUS + Advanced Boosters (min max)
future configurations improve C3 50.00 Exis ng Launch Vehicles
(mt) Europa Class Mission
performance even further. 40.00 5m x 19m 8.4m x 19m 10m x 31m Mass (300 m3) (620 m3) (1800 m3)
30.00 System ' Higher departure energy offers more
20.00 Payload
launch opportunities. Net 10.00 ' Trade space exists between 0.00 departure energy and mass 10 0 10 20 30 40 50 60 70 80 90 100 110 120 130 140 150 Characteris c Energy, C3 (km2/s2) capability.
7 www.nasa.gov/sls Game-Changing Capability
MISSION FAILURE 2016 MARS OBSERVER EXOMARS PHOBOS 2 1992 (PARTIAL SUCCESS) FUTURE • Returned some data. PHOBOS 1 MISSIONS • Lost contact before 2013
deploying lander. 1988 PHOBOS 2 MAVEN
VIKING 1 2011 MARS 6 1975 VIKING 2 PHOBOS-GRUNT / YINGHUO-1 (PARTIAL SUCCESS) MARS SCIENCE LABORATORY (CURIOSITY) CURIOSITY (SUCCESS) • Lander produced MARS 7 data during descent, • Landed August 6, 2012 • Failed before landing. MARS 6 2007
1973 MARS 5 PHOENIX MARS LANDER DAWN MARS 4 DAWN (Mars Gravity Assist) • Arrived Vesta July 2011 • Arrive Ceres MARS 5 MARINER 9 February 2015 (PARTIAL SUCCESS) MARS 3 2005 • Returned 60 images. MARS RECONNAISSANCE ORBITER MRO MARS 2 (SUCCESS)
• Failed after nine days. 1971 KOSMOS 419 • Science operations - MARINER 8 Nov. 2006 – Nov. 2008
2004 • High Resolution Imaging ROSETTA (Low Altitude Pass) Science Experiment MARS 1969B • Communication Relay MARS 3 MARS 1969A Spirit/ (PARTIAL SUCCESS) 1969 MARINER 7 MARS EXPLORATION ROVER: OPPORTUNITY • Orbiter obtained eight MARINER 6 2003 Opportunity months of data. MARS EXPLORATION ROVER: SPIRIT (SUCCESS) • Lander landed but MARS EXPRESS / BEAGLE 2 • Opportunity – Nine gathered only ROVER years and counting, 20 seconds of data. ZOND 3 (Lunar Flyby)
1965 near Endeavor crater. • First successful
LANDER 2001 • Spirit – remains silent landing on Mars. MARS ODYSSEY at its home base, Troy. ZOND 2 MARINER 3 ORBITER MARINER 4 1964 MARINER 4 1999 (SUCCESS) MARS POLAR LANDER/ • Returned 21 images. FLYBY DEEP SPACE 2 PROBES • First successful flyby. KOSMOS 21 1963
MARS CLIMATE ORBITER 1998 SPUTNIK 24 NOZOMI MARS 1 1962 SPUTNIK 22
MARS PATHFINDER 1996 MARSNIK 2 MARS 96
1960 MARSNIK 1 MARS GLOBAL SURVEYOR
European United Soviet Union/ Russia/ Japan Space States Russia China Agency Mission Flyby Lander Orbiter Rover Failure www.nasa.gov/sls 8302 Science in Society.8 Case Study: Mars Fly-By
500-600-day free-return fly-by ' Even the Initial configuration of SLS offersof Mars;orders of 2021 magnitude window greater would payload-to-destinationinclude fly-by ofenergy Venus. compared to existing launch vehicles; future configurations improve C3 performanceSLS is uniquelyeven further. capable of providing the required mass-to- ' Higherdeparture-energy departure energy offers needed more for launch opportunities. the mission. ' Trade space exists between departure energy and mass capability.
9 www.nasa.gov/sls Benefit: SLS Mass Lift Capability
Medium/Intermediate Heavy Super Heavy
Retired 300’
' SLS initial
configuration offers 200’ 70 t to LEO. Retired
' Future configurations 100’ offer 105 and 130 t to LEO.
ULA SpaceX ULA NASA NASA NASA NASA ' Mass capability Atlas V 551 Falcon 9 Delta IV H Space Shuttle Saturn V 70 t 130 t benefits mean larger 160 1800 140 1600 payloads to any Payload Volume (m 120 1400 destination. 1200 100 1000 80 800 60 600
40 3 Payload Mass (mT) Mass Payload 400 ) 20 200 0 0
Mass (mT) Volume (m3) www.nasa.gov/sls Benefit: Unrivaled Payload Volume
' SLS is investigating utilizing existing fairings for early cargo flights, offering payload envelope compatibility with design for current EELVs
' Phase A studies in work for 8.4m and 10 m fairing options
4m x 12m 5m x 14m 5m x 19m 8.4m x 31m 10m x 31m (100 m3) (200 m3) (300 m3) (1200 m3) (1800 m3) 11 www.nasa.gov/sls Case Study: Mars Sample Return
Robotic precursor mission to return material samples from Mars
70-t SLS could support one- launch Mars Sample return mission with sampling rover carrying ascent vehicle and in- space return vehicle
SLS could support two-flight sample return in conjunction with 2020 Mars science rover mission, launching ascent vehicle and in- space return vehicle Source: Mars Program Planning Group, September 2012
www.nasa.gov/sls 8355_TEDx_.12 Case Study: Martian Moons
Provides stepping-stone opportunity toward human landing on Mars
Allows for real-time human- robotic telepresence exploration of Martian surface
Provides ambitious Mars-vicinity target while developing Martian EDL capability
SLS offers mass and volume capability for needed habitation and propulsion systems
8302 Science in Society.13 wwwwww.nasa.g nasaov/sls gov/sls Case Study: NASA DRA5
NASA’s 2009 Design Reference Architecture 5 outlines plan for 900-day human mission to Mars
DRA5 requires 825 metric tons initial mass to low Earth orbit (almost double ISS launch mass).
SLS exceeds DRA5 minimum 125+ t to LEO mass launch requirement
SLS meets DRA5 minimum 10-m- diameter fairing requirement
SLS enables crewed mission to Mars as outlined by DRA5 Source: “Human Exploration of Mars Design Reference Architecture 5.0,” NASA Mars www.nasa.gov/sls Architecture Steering Group, July 2009 8355_TEDx_.14 Recent Progress
Launch Vehicle Stage Adapter: Contract MPCV-to-Stage Adapter: awarded in February 2014. First flight hardware currently in Florida for Exploration Flight Test-1 in Fall 2014. Avionics: Avionics “first light” marked in January 2014; currently testing most powerful flight system computer processor ever. Core Stage: Initial confidence barrels and domes completed; Vertical Assembly Center installation to be completed in July 2014.
Boosters: Forward Skirt test completed May 2014; preparations underway for QM-1.
Engines: First RS-25 engine fitted to A-1 stand at Stennis Space Center; testing begins October 2014. www.nasa.gov/sls Building to Exploration Mission-1 (EM-1)
09/2011 Tested Booster Development Motor
07/2012 Delivered RS 25 Engines to Inventory
07/2013 Competed Preliminary Design Review
10/2011 12/2013 Tested SLS Wind Tunnel Models
07/2013 Completed First Confidence Barrel Section Welding
10/2013 Completed Thrust Vector Control Test
11/2013 Conducted Adaptive Augmenting Control Flight Test
ACCOMPLISHMENTS 12/2013 Completed LOX Forward Dome Manufacturing Demo
1/2014 Conducted Avionics “First Light” in Integration Facility
02/2014 Shipped Multi Purpose Crew Vehicle Stage Adapter for EFT 1
07/2014 Complete Manufacturing Tooling Installation
07/2014 15 Test Main Engines, Boosters , & Core Stage Structure
07/2015 Complete the SLS Critical Design Review
06/2016 Assemble the Core Stage Assembly and Test Fire
WHAT’S NEXT 07/2017 Stack the SLS Vehicle
12/2017 Transport SLS from the VAB to the Launch Pad
16 www.nasa.gov/sls Man cannot discover new oceans unless he has the courage to lose sight of the shore.
For More Information
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www.nasa.gov/sls 8442_IAC.17