Glushko Lox/LCH4 rocket engine. 2138 kN. Isp=356s. Proposed methane-variant of RD-191. Gimbaling +/- 8 degree in two planes. In 1996 prototype development was estimated to take four years from go-ahead. Nozzle expansion ratio is 262/0.75=349.
Engine: 3,300 kg (7,200 lb). Chamber Pressure: 257.00 bar. Thrust to Weight Ratio: 66.06. Oxidizer to Fuel Ratio: 3.5.
Status: Developed 1996-.
More... - Chronology...
Unfuelled mass: 3,300 kg (7,200 lb).
Height: 4.05 m (13.28 ft).
Diameter: 2.00 m (6.50 ft).
Thrust: 2,138.00 kN (480,641 lbf).
Specific impulse: 356 s.
Specific impulse sea level: 330 s.
First Launch: 1996-.
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.
Katorgin, B; Klepikov, I, "Metanovye ZhRD NPO Energomash im. V.P. Glushko", Aviapanorama, 7-8/98, Moscow, 1998.
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