Encyclopedia Astronautica

Glushko Lox/LCH4 rocket engine. 167 kN. Riksha-0 stage 1. Design concept 1990's. Isp=351s. LOX/Methane engine derived from RD-120. Gimbaling +/- 8 degree in two planes. In 1996 prototype development was estimated to take four years from go-ahead.

Nozzle expansion ratio was 150/0.51=294.

Application: Riksha-0 stage 1.


Engine: 215 kg (473 lb). Chamber Pressure: 147.00 bar. Thrust to Weight Ratio: 79.06. Oxidizer to Fuel Ratio: 3.4.

Status: Design concept 1990's.
Unfuelled mass: 215 kg (473 lb).
Height: 1.70 m (5.50 ft).
Diameter: 0.50 m (1.64 ft).
Thrust: 167.00 kN (37,543 lbf).
Specific impulse: 351 s.
Specific impulse sea level: 309 s.

More... - Chronology...

Associated Countries
See also
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...

Associated Propellants
  • 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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