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STME
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Designer: Rocketdyne. Propellants: Lox/LH2. Thrust(vac): 2,890.000 kN (649,690 lbf). Thrust(sl): 2,450.300 kN (550,849 lbf). Isp: 431 sec. Isp (sea level): 365 sec. Mass Engine: 3,600 kg (7,900 lb). Diameter: 2.31 m (7.57 ft). Length: 3.86 m (12.66 ft). Chambers: 1. Chamber Pressure: 155.10 bar. Area Ratio: 45.00. Oxidizer to Fuel Ratio: 6.00. Thrust to Weight Ratio: 81.86. Country: USA. Status: Study 1984. Space Transportation Main Engine. Rocketdyne was teamed with Aerojet and Pratt & Whitney on the STME, which was to have powered the next generation of large launch vehicles.. Life: design life of 10 missions, 99% design reliability and 100% - 99.995% Cat I probability. Dry Mass: 3600 kg. Length: 386 cm. Nozzle Diameter: 231 cm. Engine Cycle: gas generator. Mixture Ratio: 6.0:1. Thrust: step dual thrust 2890 kN at 100%, and 2020 kN at 70% vacuum. Isp: 430.5 sec at 100%, and 429.3 sec at 70%. Expansion Ratio: 45:1. Chamber Pressure: 153.1 atm.
STME used on Rocket Stages - Used on stage: ALS. on launch vehicle: ALS.
- Used on stage: ALS. on launch vehicle: ALS.
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© Mark Wade, 1997 - 2007 except where otherwise noted.
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