Kosberg N2O4/UDMH rocket engine. 582.1 kN. Proton stage 2. Out of Production. Variant of RD-0210 providing tank pressurization. Staged combustion cycle. Isp=326s.
Application: Proton stage 2.
Thrust (sl): 421.900 kN (94,847 lbf). Thrust (sl): 43,020 kgf. Engine: 566 kg (1,247 lb). Chamber Pressure: 147.00 bar. Area Ratio: 81.3. Thrust to Weight Ratio: 104.87.
AKA: RD-468; RD-0211; 8D412K.
More... - Chronology...
Status: Out of Production.
Unfuelled mass: 566 kg (1,247 lb).
Height: 2.33 m (7.64 ft).
Diameter: 1.47 m (4.82 ft).
Thrust: 582.10 kN (130,861 lbf).
Specific impulse: 327 s.
Burn time: 230 s.
First Launch: 1962-65.
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, Visit to the museum of Chemical Automatics Design Bureau, Voronezh 1992 via Dietrich Haeseler.
Proton K-2 N2O4/UDMH propellant rocket stage. Loaded/empty mass 167,828/11,715 kg. Thrust 2,399.22 kN. Vacuum specific impulse 327 seconds. More...
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