Encyclopedia Astronautica

Kosberg Lox/LCH4 rocket engine. 836 kN. Design concept 1996-. Proposed variant of RD-0256 engine using LOX-liquid methane instead of N2O4/UDMH as propellants. Isp=353s.

Engine: 770 kg (1,690 lb). Chamber Pressure: 176.00 bar. Thrust to Weight Ratio: 110.71. Oxidizer to Fuel Ratio: 3.4.

Status: Design concept 1996-.
Unfuelled mass: 770 kg (1,690 lb).
Thrust: 836.00 kN (187,940 lbf).
Specific impulse: 353 s.
First Launch: 1996-.

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Associated Countries
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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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