Kosberg Lox/LNG rocket engine. 2251 kN. stage 1. Developed 1998-on. Proposed engine for LOX/liquid natural gas. Staged combustion cycle. Obviously variant of RD-0141 with larger nozzle. Isp=353s.
Application: stage 1.
Engine: 1,973 kg (4,349 lb). Thrust to Weight Ratio: 116.32.
Status: Developed 1998-on.
More... - Chronology...
Unfuelled mass: 1,973 kg (4,349 lb).
Height: 3.35 m (10.99 ft).
Thrust: 2,251.00 kN (506,044 lbf).
Specific impulse: 353 s.
Specific impulse sea level: 323 s.
First Launch: 1998-.
Associated Manufacturers and Agencies
Kosberg Russian manufacturer of rocket engines. Kosberg Design Bureau, Russia. More...
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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