Glushko Lox/LCH4 rocket engine. 19.6 kN. Upper stage. Developed 1993-1996. Isp=380s. Methane version of lox / kerosene upper stage engine RD-161. Gimbaling +/- 6 degree in two planes.
In 1996 the RD-161 prototype had been completed, development of a methane version was estimated to take four years. Nozzle expansion ratio is 120/0.05=2400.
Application: Upper stage.
Engine: 129 kg (284 lb). Chamber Pressure: 118.00 bar. Area Ratio: 352. Thrust to Weight Ratio: 15.5. Oxidizer to Fuel Ratio: 3.69.
Status: Developed 1993-.
More... - Chronology...
Unfuelled mass: 129 kg (284 lb).
Height: 1.70 m (5.50 ft).
Diameter: 0.76 m (2.51 ft).
Thrust: 19.60 kN (4,406 lbf).
Specific impulse: 381 s.
Burn time: 900 s.
First Launch: 1993-.
Associated Manufacturers and Agencies
Glushko Russian manufacturer of rocket engines and rockets. Glushko Design Bureau, Russia. More...
Lox/LCH4 Liquid oxygen was the earliest, cheapest, safest, and eventually the preferred oxidiser for large space launchers. Its main drawback is that it is moderately cryogenic, and therefore not suitable for military uses where storage of the fuelled missile and quick launch are required. Liquid methane has been proposed as a propellant by the Russians. More...
Klepikov, Katorgin, Chvanov, "The New Generation of Rocket Engines, Operating by Ecologically Safe Propellant ...", IAF-Congress Turin, 1997, IAF-97-S.1.03 via Dietrich Haeseler.
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