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Todd May Program Manager, Space Launch System

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Todd May Program Manager, Space Launch System SPACE LAUNCH SYSTEM AND Todd May Program Manager, Space Launch System August 2014 Mars Is The Mission 8602_Mars Society_T.May.2 Mars: The Human Destination Mars Landing: Heading for the High Ground Courtesy of Dan Durda 8602_Mars Society_T.May.3 The Journey to Mars 8602_Mars Society_T.May.4 Mars Is The World’s Mission 8602_Mars Society_T.May.5 Revolutionary Evolution 5, 8.4 or 10 Meter Payload Fairings Orion Interim Cryogenic Upper Stage Propulsion Stage Core Stage Block I Block II 70 metric tons 130 metric tons Five-Segment Liquid or Solid Solid Rocket Boosters Advanced Boosters 4 RS-25 Engines 8602_Mars Society_T.May.6 Benefit: High Departure Energy ! The Initial configuration of SLS offers orders of magnitude Cargo& Flyby& greater payload-to-destination 70.00# SLS#Block#1#+#Orion#+#iCPS# energy compared to existing SLS#Block#1#+#5.0m#Fairing#+#iCPS# 60.00# launch vehicles; future SLS#Block#1B#+#8.4m#Fairing#+#EUS# SLS#Block#2B#+#8.4m#Fairing#+#EUS#+#AdvancEd#Boosters#(min+max)# configurations improve C3 50.00# ExisKng#Launch#VEhiclEs# performance even further. Europa#Class#Mission# 40.00# 5m#x#19m# 8.4m#x#19m# 10m#x#31m# (300#m3)# (620#m3)# (1800#m3)# # # # 30.00# ! Higher departure energy offers more launch opportunities. 20.00# Net$Payload$System$Mass$(mt)$ 10.00# ! Trade space exists between 0.00# +10# 0# 10# 20# 30# 40# 50# 60# 70# 80# 90# 100# 110# 120# 130# 140# 150# departure energy and mass Characteris6c$Energy,$C3$(km2/s2)$ capability. 8602_Mars Society_T.May.7 Game-Changing Capability MISSION FAILURE 2016 MARS OBSERVER EXOMARS PHOBOS 2 1992 (PARTIAL SUCCESS) • Returned some data. • Lost contact before PHOBOS 1 2013 deploying lander. 1988 PHOBOS 2 MAVEN VIKING 1 2011 2011 MARS 6 1975 VIKING 2 PHOBOS-GRUNT / YINGHUO-1 (PARTIAL SUCCESS) MARS SCIENCE LABORATORY (CURIOSITY) CURIOSITY • Lander produced (SUCCESS) MARS 7 data during descent, • Landed August 6, 2012 • Failed before landing. MARS 6 PHOENIX MARS LANDER 2007 1973 MARS 5 DAWN MARS 4 DAWN (Mars Gravity Assist) • Arrived Vesta July 2011 • Arrive Ceres MARS 5 MARINER 9 February 2015 2005 (PARTIAL SUCCESS) MARS 3 • Returned 60 images. MARS RECONNAISSANCE ORBITER MRO MARS 2 • Failed after nine days. (SUCCESS) 1971 KOSMOS 419 • Science operations - Nov. 2006 – Nov. 2008 MARINER 8 2004 • High Resolution Imaging ROSETTA (Low Altitude Pass) Science Experiment MARS 1969B • Communication Relay MARS 3 MARS 1969A Spirit/ (PARTIAL SUCCESS) 1969 MARINER 7 • Orbiter obtained eight MARS EXPLORATION ROVER: OPPORTUNITY 2003 MARINER 6 Opportunity months of data. MARS EXPLORATION ROVER: SPIRIT (SUCCESS) • Lander landed but MARS EXPRESS / BEAGLE 2 • Opportunity – Nine gathered only ROVER years and counting, ZOND 3 (Lunar Flyby) 20 seconds of data. near Endeavor crater. • First successful 1965 2001 • Spirit – remains silent landing on Mars. LANDER MARS ODYSSEY at its home base, Troy. ZOND 2 MARINER 3 ORBITER 1964 MARINER 4 MARINER 4 1999 (SUCCESS) MARS POLAR LANDER/ • Returned 21 images. FLYBY DEEP SPACE 2 PROBES • First successful flyby. KOSMOS 21 1963 1998 MARS CLIMATE ORBITER 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 Agency China Mission Flyby Lander Orbiter Rover 8602_Mars Society_T.May.8 Failure Case Study: Mars Fly-By ! 500-600-day free-return fly-by of Mars; 2021 window would include fly-by of Venus. ! SLS is uniquely capable of providing the required mass-to- departure-energy needed for the mission. 8602_Mars Society_T.May.9 Benefit: High Mass-Lift Capability Medium/Intermediate Heavy Super Heavy Re#red& 300’& ! SLS initial configuration 200’& offers 70 t to LEO. Re#red& ! Future 100’& configurations offer 105 and 130 t to LEO. ULA&& SpaceX& ULA& NASA& NASA& NASA& NASA& Atlas&V&551& Falcon&9& Delta&IV&H& Space&SHuIle& Saturn&V& 70&t&& 130&t& ! Mass capability benefits mean 160& 1800& 140& 1600& larger payloads to Payload'Volume'(m 120& 1400& 1200& any destination. 100& 1000& 80& 800& 60& 600& 3 Payload'Mass'(mT)' 40& 400& )' 20& 200& 0& 0& 3 Mass&(mT)& Volume&(m )& 8602_Mars Society_T.May.10 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) 8602_Mars Society_T.May.11 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 8602_Mars Society_T.May.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 8602_Mars Society_T.May.13 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 and meets DRA5 minimum 10-m-diameter fairing requirement. 8602_Mars Society_T.May.14 July 2009 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. 8602_Mars Society_T.May.15 Building Toward First Flight 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 12/2013 Completed LOX Forward Dome Manufacturing Demo ACCOMPLISHMENTS 1/2014 Conducted Avionics “First Light” in Integration Facility 02/2014 Shipped Multi-Purpose Crew Vehicle Stage Adapter for EFT-1 CURRENT Complete Manufacturing Tooling Installation 10/2014-15 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 07/2017 Stack the SLS Vehicle WHAT’S NEXT WHAT’S 12/2017 Transport SLS from the VAB to the Launch Pad 8602_Mars Society_T.May.16 .
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