Transtar
Engine · USA
Original archive entry. The text, images and links below are kept as they were written.
Aerojet N2O4/MMH rocket engine. Development completed 1987. Upper stage engine using injectors, chamber, and nozzle derived from the Shuttle OMS system, but pump-fed for increased chamber pressure and Isp. Tested; no production.
The Transtar system was an upper stage engine using injector(s), chamber, and nozzle derived from the OMS system. These propellants are pump-fed which increase chamber pressure and Isp. They also permit the use of low-pressure lightweight tanks.. Manufacturer: Aerojet Propulsion Division. Applications: upper stage. Mounting: gimbaled ( 10 degrees by two electromechanical actuators. Mixture Ratio: 1.8:1. Cooling Method: fuel regenerative for chamber, radiative for extension. Burn Time: not available, 15 starts.
Engine: 76 kg (167 lb). Chamber Pressure: 23.80 bar. Area Ratio: 132. Thrust to Weight Ratio: 22.36.
Related
- Family
- Storable liquid
- Country
- USA
- Propellants
- N2O4/MMH
- Agency
- Aerojet