SSME Study (original) (raw)
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SSME Study
Notional LOx/LH2 rocket engine. Study 1967.
Status: Study 1967. Thrust: 1,535.20 kN (345,127 lbf). Specific impulse: 459 s. Specific impulse sea level: 359 s. Burn time: 379 s.
Thrust (sl): 1,200.700 kN (269,928 lbf). Thrust (sl): 122,443 kgf.
Country: USA. Launch Vehicles: S series sounding rockets, Spacemaster, Shuttle FR-3, Shuttle LS A, Shuttle NAR A, Shuttle MDC, Shuttle HCR, Shuttle LCR, Shuttle DC-3, Shuttle R134C, Shuttle LS200, Shuttle H33. Propellants: Lox/LH2. Stages: Spacemaster-1, Spacemaster-2, Shuttle FR-3-1, Shuttle FR-3-2, Shuttle HCR-1, Shuttle HCR-2, Shuttle LCR-1, Shuttle LCR-2, Shuttle LS A-1, Shuttle LS A-2, Shuttle MDC-A-1, Shuttle MDC-A-2, Shuttle NAR A-1, Shuttle NAR A-2, Shuttle DC-3-1, Shuttle DC-3-2, Shuttle R134C-1, Shuttle R134C-2, Shuttle R134G-1, Shuttle R134G-2, Shuttle H33-1, Shuttle H33-2, Shuttle LS200-1.
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