Kosberg N2O4/UDMH rocket engine. 123.6 kN. sea-based missile booster stage developed 1977-83. Isp=302s. First concept planned N2O4/kerosene as propellant, but changed to N2O4/UDMH. Single ignition, 297 development tests. 50 engines for sale.
Max. duration 420 s.
Application: sea-based missile booster stage (Burlak ?).
Engine: 120 kg (260 lb). Chamber Pressure: 196.20 bar. Thrust to Weight Ratio: 105.03.
Status: Developed 1977-83.
More... - Chronology...
Unfuelled mass: 120 kg (260 lb).
Height: 0.88 m (2.89 ft).
Diameter: 0.27 m (0.89 ft).
Thrust: 123.60 kN (27,786 lbf).
Specific impulse: 303 s.
Burn time: 60 s.
First Launch: 1977-83.
Associated Manufacturers and Agencies
Kosberg Russian manufacturer of rocket engines. Kosberg Design Bureau, Russia. More...
N2O4/UDMH Nitrogen tetroxide became the storable liquid propellant of choice from the late 1950's. Unsymmetrical Dimethylhydrazine ((CH3)2NNH2) became the storable liquid fuel of choice by the mid-1950's. Development of UDMH in the Soviet Union began in 1949. It is used in virtually all storable liquid rocket engines except for some orbital manoeuvring engines in the United States, where MMH has been preferred due to a slightly higher density and performance. More...
Burya article, Lavochkin web site.
Haeseler, Dietrich, CADB-information leaflets, International Aerospace Show Berlin 1998 (ILA 98) via Dietrich Haeseler.
Russian Arms Catalogue, Vol 5 and 6, Military Parade, Moscow via Dietrich Haeseler.
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