18
7032.1
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 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
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.
7032.4
Launch Vehicle Comparison
121 klbm to Trans-Lunar Injection147 klbm to TLI in Dual Launch Mode with CLV
112kblm to Trans-Lunar Injection
Cargo Launch Vehicle Saturn V
Height: 364 ftGross Liftoff Mass: 6.5Mlb
Lander
S-IVB (1 J-2)240 klb LOx/LH2
S-II (5 J-2)1 Mlb LOx/LH2
S-IC (5 F-1)3.9 Mlb LOx/RP
Lander
Earth Departure Stage (1 J-2X)450 klb LOx/LH2
Core Stage (5 SSME)2.2 Mlb LOx/LH2
5Segment
RSRM
Crew
Height: 358 ftGross Liftoff Mass: 6.4Mlb
Crew Launch Vehicle
55 klbm to LEO
Upper Stage (1 J-2X)
280 klb LOx/LH2
Height: 309 ftGross Liftoff Mass: 2.0Mlb
7032.5
CLV Upperstage Earth Departure Stage
ManufacturingCommon Practices / Techniques
Al-Li TanksTPS Systems
Avionics / SoftwareCommon Engine Controller / Sequencer
Main Propulsion Systems Some Common Components
Common Engine Interfaces / Inlet Conditions
Thrust Vector ControlCommon TVC Development / Test Programs
EngineCommon 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
7032.6
“1.5 Launch” Earth Orbit / Lunar Orbit Rendezvous
Ascent Stage Expended
ED
S,
LS
AM
CE
V
Earth Departure Stage Expended
LSAM Performs LOI
MOONMOON
EARTHEARTH
100 km Low Lunar Orbit
Direct EntryLand Landing
Service Module ExpendedLow
Earth Orbit
Vehicles Not to Scale
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
7032.8
~25-mT payload capacity 2-Mlb gross liftoff weight 309 ft in length
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
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
7032.9
Vehicle Configuration – Expanded View
Aft Skirt
8 BSM
Interstage Cylinder
FrustumConical Aeroshell
Short Forward Skirt (Avionics)
Forward Segment
3 Center Segments
Aft Segment and Nozzle
CEV Side Spacecraft Adapter
CLV Side Instrument Unit
CEVLAS
Systems Tunnel
2 Roll Control Pods
J2X
Thrust Structure-Aft Skirt-Thrust Cone
2 RCS PodsIntertank
LH2 Tank- Frames and Baffles- Skins- Insulation
Forward Skirt
LOX Tank- Frames and Baffles- Skins- Insulation
Systems Tunnel
Forward Skirt Extension (Recovery System)
7032.10
New Structures SubsystemsFrustum Forward Skirt
Aero Shell Fwd Skirt Extension
Modified Recovery SubsystemsAltitude Sensing Hardware, Main Chutes, Reefing Line Cutters, Pyro Release LSC and Pyro Thrusters
Pilot and Drogue Chutes
Pyro Separation Release SubsystemUpper Stage Release During Ascent 1st Stage deceleration at ReleaseFrustum ejection from 1st stage at Apogee
Electrical and Instrumentation Subsystem
Range Safety Subsystem
New Aft Motor Segment LSC
Ground Power/Control Cables T-0 Umbilical Up Systems TunnelBSMs
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
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
7032.12
CLV Configuration
Vehicle Concept Characteristics
Booster StagePropellants
Useable PropellantJettison Mass
# Boosters / TypeThrust/Weight (@ 0.6 sec)
Burn RatePMBT
PBAN1,397,785 lbm223,425 lbm1/5-Segment SRM1.7290.368 inch/sec60°F
Gross Lift-Off Weight (GLOW)Payload
Launch Escape SystemLength
Delivery Orbit
2,006,839 lbm5.5 m diameter, Block 1A CEV13,288 lbm309 ft-30 x 100 nmi @ 28.5°, 51.6°
Second StagePropellants
Ascent PropellantDry Mass
# Engines / TypeEngine Thrust (100%)
Engine Isp (100%)Mission Power Level
Thrust/Weight @ ignition
LOX/LH2
279,877 lbm31,545 lbm1/J-2X273,750 lbf @ Vac448 s @ Vac100%0.985
7032.13
Reference Missions (28.5°/ 51.6°)
Launch SRBSplashdown
Maximum Dynamic PressureTime 48.9 sec
Altitude 29,611 feetMach 1.63/1.63
Dynamic Pressure 759/767 psf
SRB SeparationTime 131.56 sec
Altitude 195,607/197,324 feetMach 6.13/6.17
Max Altitude 314,324/319,143 feet
MECOTime 595.1 sec
Burn Duration 463.54 secPayload Separation
Maximum Axial Acceleration3.2/3.22 g
LiftoffTime 0.6 sec
Thrust-to-Weight 1.72/1.73GLOW 2,006,839/2,003,245 lbm
Main Engine StartTime 133
LAS JettisonTime 167.6 sec
Altitude 280,763/283,734 feetMach 7.54/7.58
UpperstageImpact
7032.14
CLV Size Comparison to Shuttle
Representations to Scale
7032.15
J-2X Assembly
Upper Stage
Nozzle
Single Engine Test
Assembly, Refurb & Test ARF/ASTF
Flight
Aft SegmentFWD & Center
SegmentsDisassemblyHangar AF
Rail Transport Utah Facility
First Stage Recovery
Interstage
Kennedy Space Center
Michoud Assembly Facility
RCS
PRF Parachute
Stacking RPSF
FWD Frustum
FWD Frustum
FWD & CenterSegments
Aft Segment
Aft Skirt
Preliminary CLV Manufacturing / Refurbishment Flow
Barge
Stennis Space Center
7032.16
2005 2006 2007 2008 2009 2010 2011 2012 2013Name
Constellation Level II Milestones
Vehicle Integration
First Stage
1st StageFab, Integ & Test
Upperstage
US Fab, Integ & Test (Dev and Flt Units)
Flt Software
Upperstage Engine
US Fab, Integ & Test
Avionics
Ground Vibration Test
Suborbital Flight Test
L1 DPMS
RBRStarts
SRR Starts
PDR TBD
CDRTBD
Sub-OrbitalFT-1
Sub-OrbitalFT-2
OFT-1OFT-2
HF-1
HF-2
HF-3
UMC-1
SRR Board PDR Board CDR Board Dec Pt System DCR
Pre-SRR
SRR Board
PDR Board ICDR CDR Board DCR DDCR DDDCR
Sub Orbital FT-1 OFT-1 OFT-2
HF-1
SRR Board PDR Board CDR Board Flight Design Verification
Dec PtDCR
STA SFT-1 MPTA OFT-1 OFT-2
OFT-3
OFT-4
OFT-5
SWSRR PDR Board ICDR CDR Board OFT-1
OFT-2
OFT-3
OFT-4
OFT-5
SRR Board PDR Board CDR Board Flight Design VerificationDCR
MPTA
OFT-1
OFT-2 OFT-3
OFT-4
OFT-5
SRR PDR Board CDR BoardFlt S/W
V&V
TS 4550ATP
Test RqmtsDefined
HW @TS4550
SFT GVTComplete
HW @TS4550
HF GVTComplete
SRRBoard PDR Board CDR Board
SFT-1
Crew Launch VehicleDraft Summary Schedule (CY)
= Delivery to KSC
7032.17
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
