Encyclopedia Astronautica
Transtar


Aerojet N2O4/MMH rocket engine. 16.7 kN. Development completed 1987. Isp=328s. 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: gimballed ( 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.

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

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Associated Countries
See also
Associated Manufacturers and Agencies
  • Aerojet American manufacturer of rockets, spacecraft, and rocket engines. Aerojet, Sacramento, CA, USA. More...

Associated Propellants
  • N2O4/MMH Nitrogen tetroxide became the storable liquid propellant of choice from the late 1950's. Monomethylhydrazine (CH3NHNH2) is a storable liquid fuel that found favour in the United States for use in orbital spacecraft engines. Its advantages in comparison to UDMH are higher density and slightly higher performance. More...

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