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STME
Part of SSME Family
Rocketdyne LOx/LH2 rocket engine. Cancelled 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.

Status: Study 1984. Thrust: 2,890.00 kN (649,690 lbf). Unfuelled mass: 3,600 kg (7,900 lb). Specific impulse: 431 s. Specific impulse sea level: 365 s. Height: 3.86 m (12.66 ft). Diameter: 2.31 m (7.57 ft).

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.

Thrust (sl): 2,450.300 kN (550,849 lbf). Thrust (sl): 249,864 kgf. Engine: 3,600 kg (7,900 lb). Chamber Pressure: 155.10 bar. Area Ratio: 45. Thrust to Weight Ratio: 81.8605515418392. Oxidizer to Fuel Ratio: 6. Coefficient of Thrust vacuum: 2.00247996549448. Coefficient of Thrust sea level: 1.70836231843566.



Country: USA. Launch Vehicles: Shuttle LRB, ALS, NLS, NLS HLV. Propellants: Lox/LH2. Stages: Shuttle LRB stage, ALS stage, NLS Core, NLS HLV stage, NLS Semistage. Agency: Rocketdyne.

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