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SSME Study
Part of SSME
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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