2 Exploration Launch Office Scope Crew Launch VehicleSingle 5 segment RSRB/M 1st stageUpper stage powered by a single engine derived from the Saturn J-2Cargo Launch VehicleTwin 5 segment RSRB/M 1st stage (from CLV)Core stage derived from the External TankPowered by 5 low cost SSMEsCLV-derived avionicsEarth Departure StageUpper stage derived from the External TankPowered by a single CLV upper stage engine -2 burn capabilityCLV-derived main propulsion systems and avionicsFuture development
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.
5 Upper Stage Synergies CLV Upperstage Earth Departure Stage Manufacturing Common Practices / Techniques Al-Li TanksTPS SystemsCLV UpperstageEarth Departure StageAvionics / Software Common Engine Controller / SequencerMain Propulsion Systems Some Common Components Common Engine Interfaces / Inlet ConditionsThrust Vector Control Common TVC Development / Test ProgramsEngineCommon Engine Development / Test ProgramsCommon Test Facilities (MPTA/Battleship)Testing Common Engine Development / Test ProgramsPossible flight testbed of CFM and Restart
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 Overall CLV System Element Description ~25-mT payload capacity2-Mlb gross liftoff weight309 ft in lengthFirst StageDerived from current Shuttle Reusable Solid Rocket Motor/Booster (RSRM/B)Five segments/Polybutadiene Acrylonitride (PBAN) propellantRecoverableNew forward adapterUpperstage280-klb Liquid Oxygen/Liquid Hydrogen (LOX/LH2) stage5.5-m diameterAluminum-Lithium (Al-Li) structuresInstrument unit and interstageRCS / roll control for 1st stage flightCLV avionics systemUpperstage EngineSaturn J-2 derived engine (J-2X)Expendable
9 Vehicle Configuration – Expanded View Interstage CylinderFrustumConical AeroshellForward Skirt Extension (Recovery System)Short Forward Skirt (Avionics)Forward Segment8 BSM2 Roll Control Pods3 Center SegmentsLASCEVAft Segment and NozzleForward SkirtAft SkirtSystems TunnelIntertankCEV Side Spacecraft Adapter2 RCS PodsThrust StructureAft SkirtThrust ConeCLV Side Instrument UnitSystems TunnelLH2 TankFrames and BafflesSkinsInsulationJ2XLOX TankFrames and BafflesSkinsInsulation
10 5 Segment RSRM 1st Stage 5 Segment Motor Pyro Separation Release SubsystemUpper Stage Release During Ascent1st Stage deceleration at ReleaseFrustum ejection from 1st stage at ApogeeRange Safety SubsystemNew Aft Motor Segment LSCElectrical and Instrumentation SubsystemNew Structures SubsystemsFrustum Forward SkirtAero Shell Fwd Skirt ExtensionNew or Modified Avionics for TVC System Control, Range Safety Destruct, Power Distribution, Batteries, Instrumentation, Video, Pyro Initiation, Recovery System and Nozzle SeveranceModified Recovery SubsystemsAltitude Sensing Hardware, Main Chutes, Reefing Line Cutters, Pyro Release LSC and Pyro ThrustersPilot and Drogue ChutesGround Power/ Control Cables T-0 Umbilical Up Systems TunnelBSMs5 Segment Motor
11 J-2X Engine Restart of the Saturn J-2/J-2S engine J-2 powered the S-II and S-IVB270 Klbf LOx/LH2 engineUncooled nozzle extension for increased IspModern manufacturing methodsMk 29 Turbomachinery successfully restarted to power the X-33Aerospike engine in the late 90’s
18 Moon, Mars, and Beyond Summary ATK THIOKOLNASA is making great progress in implementing Exploration VisionCrew Launch Vehicle (CLV) is scheduled for initial crew launch in 2012Initial Cargo Launch Vehicle (CaLV) flight planned in 2015 timeframeKey elements of NASA and contractor teams in place and working toward SRR in Fall 2006Moon, Mars, and Beyond
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