Encyclopedia Astronautica

Glushko Lox/LCH4 rocket engine. 353 kN. Upper stage. Design concept 1990's. Isp=379s. Proposed upper stage engine, a methane variant of RD-134. Gimbaling +/- 3 degree in two planes. Four chambers with one common turbopump.

Status 1996 was project, development estimated for four years. Nozzle expansion ratio is 170/0.05=3400.

Application: Upper stage.


Chambers: 4. Engine: 570 kg (1,250 lb). Chamber Pressure: 167.00 bar. Thrust to Weight Ratio: 63.15. Oxidizer to Fuel Ratio: 3.4.

Status: Design concept 1990's.
Unfuelled mass: 570 kg (1,250 lb).
Height: 1.60 m (5.20 ft).
Diameter: 2.40 m (7.80 ft).
Thrust: 353.00 kN (79,357 lbf).
Specific impulse: 379 s.

More... - Chronology...

Associated Countries
See also
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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