Encyclopedia Astronautica

Kosberg Lox/LNG rocket engine. 147 kN. upper stage. Developed 1998-on. Proposed engine for LOX/liquid natural gas. Staged combustion cycle. Four-chamber variant of RD-0144. Isp=374s.

Application: upper stage.

Chambers: 4. Engine: 282 kg (621 lb). Thrust to Weight Ratio: 53.19.

Status: Developed 1998-on.
Unfuelled mass: 282 kg (621 lb).
Height: 1.42 m (4.65 ft).
Thrust: 147.00 kN (33,046 lbf).
Specific impulse: 374 s.
First Launch: 1998-.

More... - Chronology...

Associated Countries
See also
Associated Manufacturers and Agencies
  • Kosberg Russian manufacturer of rocket engines. Kosberg Design Bureau, Russia. More...

Associated Propellants
  • Lox/LNG 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. Liquefied natural gas - mainly methane,with traces of sulfur, etc. More...

  • Novosti kosmonavtiki, Issue 3, 1999.

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