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Transtar
Part of AJ10 Family
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.

Status: Development completed 1987. Thrust: 16.70 kN (3,754 lbf). Unfuelled mass: 76 kg (167 lb). Specific impulse: 328 s. Height: 1.27 m (4.16 ft).

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.



Family: Storable liquid. Country: USA. Propellants: N2O4/MMH. Agency: Aerojet.

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