STME
Engine · USA
Original archive entry. The text, images and links below are kept as they were written.
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.
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.
Related
- Country
- USA
- Launch Vehicles
- Shuttle LRB, ALS, NLS, NLS HLV
- Propellants
- Lox/LH2
- Agency
- Rocketdyne