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. 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. 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

5. Upper Stage Synergies CLV Upperstage Earth Departure Stage
Manufacturing Common Practices / Techniques Al-Li Tanks
TPS Systems
CLV Upperstage
Earth Departure Stage
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

6. “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

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 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

9. 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
CEV Side Spacecraft Adapter
2 RCS Pods
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

10. 5 Segment RSRM 1st Stage 5 Segment Motor
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

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. CLV Configuration Vehicle Concept Characteristics Second Stage
Propellants
Ascent Propellant
Dry Mass
# Engines / Type
Engine Thrust (100%)
Engine Isp (100%)
Mission Power Level
ignition
LOX/LH2
279,877 lbm
31,545 lbm
1/J-2X
273,750 Vac
448 Vac
100%
0.985
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°
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

13. Reference Missions (28.5°/ 51.6°)
MECO
Time sec
Burn Duration 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 sec
Altitude 280,763/283,734 feet
Mach 7.54/7.58
SRB Separation
Time 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

14. CLV Size Comparison to Shuttle
Representations to Scale

15. Preliminary CLV Manufacturing / Refurbishment Flow
Stennis Space Center
Kennedy Space Center
RCS
J-2X Assembly
Single Engine Test
Upper Stage
Flight
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
PRF
Parachute
Rail Transport Utah Facility

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

18. Moon, Mars, and Beyond 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