Kosberg lox/lh2 rocket engine. 98 kN. upper stage. Design concept 1996-. Concept for a cryogenic engine for upper stages. Derived from RD-0131, but four chambers with bell nozzles, common turbopump. Isp=469s.
Application: upper stage.
Chambers: 4. Engine: 370 kg (810 lb). Chamber Pressure: 98.00 bar. Thrust to Weight Ratio: 27.02. Oxidizer to Fuel Ratio: 5.9.
Status: Design concept 1996-.
More... - Chronology...
Unfuelled mass: 370 kg (810 lb).
Height: 1.38 m (4.52 ft).
Thrust: 98.00 kN (22,031 lbf).
Specific impulse: 469 s.
First Launch: 1996-.
Associated Manufacturers and Agencies
Kosberg Russian manufacturer of rocket engines. Kosberg Design Bureau, Russia. More...
Lox/LH2 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 hydrogen was identified by all the leading rocket visionaries as the theoretically ideal rocket fuel. It had big drawbacks, however - it was highly cryogenic, and it had a very low density, making for large tanks. The United States mastered hydrogen technology for the highly classified Lockheed CL-400 Suntan reconnaissance aircraft in the mid-1950's. The technology was transferred to the Centaur rocket stage program, and by the mid-1960's the United States was flying the Centaur and Saturn upper stages using the fuel. It was adopted for the core of the space shuttle, and Centaur stages still fly today. More...
Polovnikov S P; Karpov, A S, "Projekt 'Vozdushnyy Start'", Vestnik Aviatsii i Kosmonavtiki, Moscow, 1-2/98 via Dietrich Haeseler.
Russian Arms Catalogue, Vol 5 and 6, Military Parade, Moscow via Dietrich Haeseler.
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