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7032.1. 7032.2 Exploration Launch Office Scope  Crew Launch Vehicle  Single 5 segment RSRB/M 1st stage  Upper stage powered by a single engine derived.

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Presentation on theme: "7032.1. 7032.2 Exploration Launch Office Scope  Crew Launch Vehicle  Single 5 segment RSRB/M 1st stage  Upper stage powered by a single engine derived."— Presentation transcript:

1 7032.1

2 7032.2 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

3 7032.3 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.

4 7032.4 Launch Vehicle Comparison 121 klbm to Trans-Lunar Injection 147 klbm to TLI in Dual Launch Mode with CLV 112kblm to Trans-Lunar Injection Cargo Launch VehicleSaturn V Height: 364 ft Gross Liftoff Mass: 6.5Mlb Lander S-IVB (1 J-2) 240 klb LOx/LH 2 S-II (5 J-2) 1 Mlb LOx/LH 2 S-IC (5 F-1) 3.9 Mlb LOx/RP Lander Earth Departure Stage (1 J-2X) 450 klb LOx/LH 2 Core Stage (5 SSME) 2.2 Mlb LOx/LH 2 5 Segment RSRM Crew Height: 358 ft Gross Liftoff Mass: 6.4Mlb Crew Launch Vehicle 55 klbm to LEO Upper Stage (1 J-2X) 280 klb LOx/LH 2 Height: 309 ft Gross Liftoff Mass: 2.0Mlb

5 7032.5 CLV UpperstageEarth Departure Stage Manufacturing Common Practices / Techniques Al-Li Tanks TPS Systems Avionics / Software Common Engine Controller / Sequencer Main Propulsion Systems Some Common Components Common Engine Interfaces / Inlet Conditions Thrust Vector Control Common TVC Development / Test Programs Engine Common Engine Development / Test Programs Common Test Facilities (MPTA/Battleship) Testing Common Engine Development / Test Programs Possible flight testbed of CFM and Restart Upper Stage Synergies

6 7032.6 “1.5 Launch” Earth Orbit / Lunar Orbit Rendezvous Ascent Stage Expended EDS, LSAM CEV Earth Departure Stage Expended LSAM Performs LOI MOON EARTH 100 km Low Lunar Orbit Direct Entry Land Landing Service Module Expended Low Earth Orbit Vehicles Not to Scale

7 7032.7 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

8 7032.8  ~25-mT payload capacity  2-Mlb gross liftoff weight  309 ft in length Upperstage 280-klb Liquid Oxygen/Liquid Hydrogen (LOX/LH 2) stage 5.5-m diameter Aluminum-Lithium (Al-Li) structures Instrument unit and interstage RCS / roll control for 1st stage flight CLV avionics system First Stage Derived from current Shuttle Reusable Solid Rocket Motor/Booster (RSRM/B) Five segments/Polybutadiene Acrylonitride (PBAN) propellant Recoverable New forward adapter Upperstage Engine Saturn J-2 derived engine (J-2X) Expendable Overall CLV System Element Description

9 7032.9 Vehicle Configuration – Expanded View Aft Skirt 8 BSM Interstage Cylinder Frustum Conical Aeroshell Short Forward Skirt (Avionics) Forward Segment 3 Center Segments Aft Segment and Nozzle CEV Side Spacecraft Adapter CLV Side Instrument Unit CEV LAS Systems Tunnel 2 Roll Control Pods J2X Thrust Structure -Aft Skirt -Thrust Cone 2 RCS Pods Intertank LH2 Tank -Frames and Baffles -Skins -Insulation Forward Skirt LOX Tank -Frames and Baffles -Skins -Insulation Systems Tunnel Forward Skirt Extension (Recovery System)

10 7032.10 New Structures Subsystems Frustum Forward Skirt Aero Shell Fwd Skirt Extension Modified Recovery Subsystems Altitude Sensing Hardware, Main Chutes, Reefing Line Cutters, Pyro Release LSC and Pyro Thrusters Pilot and Drogue Chutes Pyro Separation Release Subsystem Upper Stage Release During Ascent 1 st Stage deceleration at Release Frustum ejection from 1 st stage at Apogee Electrical and Instrumentation Subsystem Range Safety Subsystem New Aft Motor Segment LSC Ground Power/ Control Cables T-0 Umbilical Up Systems Tunnel BSMs 5 Segment Motor 5 Segment RSRM 1st Stage New or Modified Avionics for TVC System Control, Range Safety Destruct, Power Distribution, Batteries, Instrumentation, Video, Pyro Initiation, Recovery System and Nozzle Severance

11 7032.11 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

12 7032.12 CLV Configuration Vehicle Concept Characteristics 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 Gross Lift-Off Weight (GLOW) Payload Launch Escape System Length Delivery Orbit 2,006,839 lbm 5.5 m diameter, Block 1A CEV 13,288 lbm 309 ft -30 x 100 nmi @ 28.5°, 51.6° Second Stage Propellants Ascent Propellant Dry Mass # Engines / Type Engine Thrust (100%) Engine Isp (100%) Mission Power Level Thrust/Weight @ ignition LOX/LH 2 279,877 lbm 31,545 lbm 1/J-2X 273,750 lbf @ Vac 448 s @ Vac 100% 0.985

13 7032.13 Reference Missions (28.5°/ 51.6°) Launch SRB Splashdown Maximum Dynamic Pressure Time 48.9 sec Altitude 29,611 feet Mach 1.63/1.63 Dynamic Pressure 759/767 psf SRB Separation Time 131.56 sec Altitude 195,607/197,324 feet Mach 6.13/6.17 Max Altitude 314,324/319,143 feet MECO Time 595.1 sec Burn Duration 463.54 sec Payload Separation Maximum Axial Acceleration 3.2/3.22 g Liftoff Time 0.6 sec Thrust-to-Weight 1.72/1.73 GLOW 2,006,839/2,003,245 lbm Main Engine Start Time 133 LAS Jettison Time 167.6 sec Altitude 280,763/283,734 feet Mach 7.54/7.58 Upperstage Impact

14 7032.14 CLV Size Comparison to Shuttle Representations to Scale

15 7032.15 J-2X Assembly Upper Stage Nozzle Single Engine Test Assembly, Refurb & Test ARF/ASTF Flight Aft Segment FWD & Center Segments Disassembly Hangar AF Rail Transport Utah Facility First Stage Recovery Interstage Kennedy Space Center Michoud Assembly Facility RCS PRFParachute Stacking RPSF FWD Frustum FWD & Center Segments Aft Segment Aft Skirt Preliminary CLV Manufacturing / Refurbishment Flow Barge Stennis Space Center

16 7032.16 Crew Launch Vehicle Draft Summary Schedule (CY) = Delivery to KSC

17 7032.17

18 7032.18 Summary  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 ATK THIOKOL Moon, Mars, and Beyond

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