Encyclopedia Astronautica

Kosberg Lox/LCH4 rocket engine. 1720 kN. Design concept 1990's. Proposed variant of the RD-0120M engine using liquid methane instead of hydrogen as propellant. Isp=372s.

Engine: 2,600 kg (5,700 lb). Chamber Pressure: 186.00 bar. Thrust to Weight Ratio: 67.45. Oxidizer to Fuel Ratio: 3.4.

Status: Design concept 1990's.
Unfuelled mass: 2,600 kg (5,700 lb).
Thrust: 1,720.00 kN (386,670 lbf).
Specific impulse: 372 s.

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Associated Countries
See also
Associated Manufacturers and Agencies
  • Kosberg Russian manufacturer of rocket engines. Kosberg 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...

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