RD-0225 Almaz engine
RD-0225 main propulsion engine for Almaz space station
Credit: © Dietrich Haeseler
Credit: © Mark Wade
Kosberg N2O4/UDMH rocket engine. 3.923 kN. Almaz space station orbital maneuvering. Hardware. Originally designed for UR-100 follow-ons spaceships. Two engines used on Almaz space station for orbital maneuvering, Pressure fed. Isp=287s. First flight 1974.
Application: Almaz space station orbital maneuvering.
Engine: 23 kg (50 lb). Chamber Pressure: 8.80 bar. Area Ratio: 64. Thrust to Weight Ratio: 17.39. Oxidizer to Fuel Ratio: 1.85.
More... - Chronology...
Unfuelled mass: 23 kg (50 lb).
Height: 1.00 m (3.27 ft).
Diameter: 0.46 m (1.50 ft).
Thrust: 3.92 kN (882 lbf).
Specific impulse: 287 s.
Burn time: 1,200 s.
First Launch: 1966-71.
Almaz APOS Russian manned space station. Cancelled 1966. The initial Almaz program planned in 1965 consisted of two phases. More...
Almaz OPS-2 Russian manned space station. Cancelled 1979. The initial Almaz military space station program planned in 1965 consisted of two phases. More...
Almaz Russian manned space station. 3 launches, 1973.04.03 (Salyut 2) to 1976.06.22 (Salyut 5). Chelomei's Almaz space station was designed to conduct orbital research into the usefulness of manned observation of the earth. More...
Almaz OPS Russian manned space station. 3 launches, 1973.04.03 (Salyut 2) to 1976.06.22 (Salyut 5). Vladimir Chelomei's Almaz OPS was the only manned military space station ever actually flown. More...
Almaz-T Russian civilian surveillance radar satellite. 3 launches, 1986.11.29 (Almaz-T s/n 303 Failure) to 1991.03.31 (Almaz 1). The results of the manned Almaz flights showed that manned reconnaissance from space was not worth the expense. More...
Almaz-1B Russian civilian surveillance radar satellite. Study 1993. More...
Almaz-2 Russian civilian surveillance radar satellite. Study 1995. Plans for an even more sophisticated and capable civilian Almaz 2 spacecraft were made in the early 1990's. Almaz 2's payload mass of 6. More...
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 KM-4 Lox/LH2 propellant rocket stage. Loaded/empty mass 19,500/3,000 kg. Thrust 73.58 kN. Vacuum specific impulse 461 seconds. Planned version for Proton. Never developed. More...
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