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Exploration Launch Office Scope

Exploration Launch Office Scope. Crew Launch Vehicle Single 5 segment RSRB/M 1st stage Upper stage powered by a single engine derived from the Saturn J-2 Cargo Launch Vehicle Twin 5 segment RSRB/M 1st stage (from CLV) Core stage derived from the External Tank Powered by 5 low cost SSMEs

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Exploration Launch Office Scope

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  1. Exploration Launch Office Scope • Crew Launch Vehicle • Single 5 segment RSRB/M 1st stage • Upper stage powered by a single engine derived from the Saturn J-2 • Cargo Launch Vehicle • Twin 5 segment RSRB/M 1st stage (from CLV) • Core stage derived from the External Tank • Powered by 5 low cost SSMEs • CLV-derived avionics • Earth Departure Stage • Upper stage derived from the External Tank • Powered by a single CLV upper stage engine - 2 burn capability • CLV-derived main propulsion systems and avionics Future development

  2. Current Launch Approach Attributes • Reduces risk for the lunar program. • Addressing critical systems sooner. • Eliminates a top ESAS identified risk (SSME airstart) and addresses another earlier (J-2 development). • Fewer launch vehicle development steps to lunar missions: • Single upperstage engine development (J-2X). • More robust upperstage engine cycle for altitude start / capable of restart - proven in Saturn. • Single solid rocket booster development (RSRM). • Single core engine development (SSME). • More ‘balanced’ engine production rate requirement between J-2X and SSME.

  3. Launch Vehicle Comparison Lander Crew Lander Earth Departure Stage (1 J-2X) 450 klb LOx/LH2 S-IVB (1 J-2) 240 klb LOx/LH2 Upper Stage (1 J-2X) 280 klb LOx/LH2 S-II (5 J-2) 1 Mlb LOx/LH2 Core Stage (5 SSME) 2.2 Mlb LOx/LH2 5 Segment RSRM S-IC (5 F-1) 3.9 Mlb LOx/RP Height: 309 ft Gross Liftoff Mass: 2.0Mlb Height: 358 ft Gross Liftoff Mass: 6.4Mlb Height: 364 ft Gross Liftoff Mass: 6.5Mlb 55 klbm to LEO 121 klbm to Trans-Lunar Injection 147 klbm to TLI in Dual Launch Mode with CLV 112kblm to Trans-Lunar Injection Crew Launch Vehicle Cargo Launch Vehicle Saturn V

  4. Upper Stage Synergies ManufacturingCommon Practices / TechniquesAl-Li Tanks TPS Systems CLV Upperstage Earth Departure Stage Avionics / SoftwareCommon Engine Controller / Sequencer Main Propulsion SystemsSome Common ComponentsCommon Engine Interfaces / Inlet Conditions Thrust Vector ControlCommon TVC Development / Test Programs Engine Common Engine Development / Test Programs Common Test Facilities (MPTA/Battleship) TestingCommon Engine Development / Test Programs Possible flight testbed of CFM and Restart

  5. “1.5 Launch” Earth Orbit / Lunar Orbit Rendezvous MOON Ascent Stage Expended LSAM Performs LOI 100 km Low Lunar Orbit Vehicles Not to Scale Earth Departure Stage Expended Service Module Expended Low Earth Orbit CEV EDS, LSAM Direct Entry Land Landing EARTH

  6. Overall Requirements and Design Philosophy • Keep it simple. • Minimize complexity and interactions. • Simplify interfaces. • Stop at “good enough”. • Make it robust. • Right size margins. • Focus on the ‘-ilities. • Focus on RM&S early. • Apply validated engineering tools, models, and data to a new vehicle configuration. • Look to Lessons Learned

  7. Overall CLV System Element Description • ~25-mT payload capacity • 2-Mlb gross liftoff weight • 309 ft in length • First Stage • Derived from current Shuttle Reusable Solid Rocket Motor/Booster (RSRM/B) • Five segments/Polybutadiene Acrylonitride (PBAN) propellant • Recoverable • New forward adapter • Upperstage • 280-klb Liquid Oxygen/Liquid Hydrogen (LOX/LH2) stage • 5.5-m diameter • Aluminum-Lithium (Al-Li) structures • Instrument unit and interstage • RCS / roll control for 1st stage flight • CLV avionics system • Upperstage Engine • Saturn J-2 derived engine (J-2X) • Expendable

  8. Vehicle Configuration – Expanded View Interstage Cylinder Frustum Conical Aeroshell Forward Skirt Extension (Recovery System) Short Forward Skirt (Avionics) Forward Segment 8 BSM 2 Roll Control Pods 3 Center Segments LAS CEV Aft Segment and Nozzle Forward Skirt Aft Skirt Systems Tunnel Intertank 2 RCS Pods CEV Side Spacecraft Adapter • Thrust Structure • Aft Skirt • Thrust Cone CLV Side Instrument Unit Systems Tunnel • LH2 Tank • Frames and Baffles • Skins • Insulation J2X • LOX Tank • Frames and Baffles • Skins • Insulation

  9. 5 Segment RSRM 1st Stage • Pyro Separation Release Subsystem • Upper Stage Release During Ascent • 1st Stage deceleration at Release • Frustum ejection from 1st stage at Apogee • Range Safety Subsystem • New Aft Motor Segment LSC Electrical and Instrumentation Subsystem • New Structures Subsystems • Frustum Forward Skirt • Aero Shell Fwd Skirt Extension New or Modified Avionics for TVC System Control, Range Safety Destruct, Power Distribution, Batteries, Instrumentation, Video, Pyro Initiation, Recovery System and Nozzle Severance Modified Recovery Subsystems Altitude Sensing Hardware, Main Chutes, Reefing Line Cutters, Pyro Release LSC and Pyro Thrusters Pilot and Drogue Chutes Ground Power/Control Cables T-0 Umbilical Up Systems Tunnel BSMs 5 Segment Motor

  10. J-2X Engine • Restart of the Saturn J-2/J-2S engine • J-2 powered the S-II and S-IVB • 270 Klbf LOx/LH2 engine • Uncooled nozzle extension for increased Isp • Modern manufacturing methods • Mk 29 Turbomachinery successfully restarted to power the X-33 Aerospike engine in the late 90’s

  11. CLV Configuration Vehicle Concept Characteristics Second Stage Propellants Ascent Propellant Dry Mass # Engines / Type Engine Thrust (100%) Engine Isp (100%) Mission Power Level Thrust/Weight @ ignition LOX/LH2 279,877 lbm 31,545 lbm 1/J-2X 273,750 lbf @ Vac 448 s @ Vac 100% 0.985 2,006,839 lbm 5.5 m diameter, Block 1A CEV 13,288 lbm 309 ft -30 x 100 nmi @ 28.5°, 51.6° Gross Lift-Off Weight (GLOW) Payload Launch Escape System Length Delivery Orbit Booster Stage Propellants Useable Propellant Jettison Mass # Boosters / Type Thrust/Weight (@ 0.6 sec) Burn Rate PMBT PBAN 1,397,785 lbm 223,425 lbm 1/5-Segment SRM 1.729 0.368 inch/sec 60°F

  12. Reference Missions (28.5°/ 51.6°) MECO Time 595.1 sec Burn Duration 463.54 sec Payload Separation Maximum Dynamic Pressure Time 48.9 sec Altitude 29,611 feet Mach 1.63/1.63 Dynamic Pressure 759/767 psf Main Engine Start Time 133 Maximum Axial Acceleration 3.2/3.22 g LAS Jettison Time 167.6 sec Altitude 280,763/283,734 feet Mach 7.54/7.58 SRB Separation Time 131.56 sec Altitude 195,607/197,324 feet Mach 6.13/6.17 Max Altitude 314,324/319,143 feet Liftoff Time 0.6 sec Thrust-to-Weight 1.72/1.73 GLOW 2,006,839/2,003,245 lbm Upperstage Impact Launch SRB Splashdown

  13. CLV Size Comparison to Shuttle Representations to Scale

  14. Preliminary CLV Manufacturing / Refurbishment Flow Stennis Space Center Kennedy Space Center RCS J-2X Assembly Single Engine Test Flight Upper Stage Michoud Assembly Facility Interstage Barge Aft Segment FWD & Center Segments Stacking RPSF Nozzle FWD Frustum First Stage Recovery FWD Frustum Assembly, Refurb & Test ARF/ASTF Aft Skirt FWD & Center Segments Aft Segment Disassembly Hangar AF Rail Transport Utah Facility PRF Parachute

  15. Crew Launch Vehicle Draft Summary Schedule (CY) = Delivery to KSC

  16. Summary ATK THIOKOL • NASA is making great progress in implementing Exploration Vision • Crew Launch Vehicle (CLV) is scheduled for initial crew launch in 2012 • Initial Cargo Launch Vehicle (CaLV) flight planned in 2015 timeframe • Key elements of NASA and contractor teams in place and working toward SRR in Fall 2006 Moon, Mars, and Beyond

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