Glushko Lox/LCH4 rocket engine. 902 kN. Riksha (-1, -2) stage 1. Developed 1994-. Isp=353s. Methane variant of RD-120K engine. Thrust range and Isp range due to throat diameter and chamber pressure. Gimbaling +/- 6 degree in two planes.
Chamber pressure 163 - 172. Status 1996 was development estimated as three years from go-ahead.
Application: Riksha (-1, -2) stage 1.
Throttled thrust(vac): 814.000 kN (182,994 lbf). Engine: 1,500 kg (3,300 lb). Chamber Pressure: 172.00 bar. Thrust to Weight Ratio: 61.33. Oxidizer to Fuel Ratio: 3.4.
AKA: RD-120M; RD-182.
More... - Chronology...
Status: Developed 1994-.
Unfuelled mass: 1,500 kg (3,300 lb).
Height: 2.80 m (9.10 ft).
Diameter: 1.50 m (4.90 ft).
Thrust: 902.00 kN (202,777 lbf).
Specific impulse: 353 s.
Specific impulse sea level: 316 s.
First Launch: 1994-.
Associated Launch Vehicles
Riksha Russian orbital launch vehicle. New design launch vehicle based on SLBM technology. More...
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.
Polovnikov S P; Karpov, A S, "Projekt 'Vozdushnyy Start'", Vestnik Aviatsii i Kosmonavtiki, Moscow, 1-2/98 via Dietrich Haeseler.
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