CADB Museum, March 1992.
Credit: © Dietrich Haeseler
Kosberg N2O4/UDMH rocket engine. 78 kN. upper stage of unnamed missile by Mishin. Developed 1965-70. Isp=330s.
Application: upper stage of unnamed missile by Mishin..
Chambers: 1 + 2. Engine: 150 kg (330 lb). Chamber Pressure: 122.60 bar. Thrust to Weight Ratio: 53.02.
Status: Developed 1965-70.
More... - Chronology...
Unfuelled mass: 150 kg (330 lb).
Height: 1.60 m (5.20 ft).
Diameter: 0.80 m (2.62 ft).
Thrust: 78.00 kN (17,535 lbf).
Specific impulse: 330 s.
Specific impulse sea level: 300 s.
Burn time: 800 s.
First Launch: 1965-70.
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...
Haeseler, Dietrich, Visit to the museum of Chemical Automatics Design Bureau, Voronezh 1992 via Dietrich Haeseler.
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