Kosberg N2O4/UDMH rocket engine. 682 kN. R-29RM / RSM-54 (SS-N-23) stage 1. Out of Production. Main engine in system RD-0243. Staged combustion cycle. Submerged in propellant tank. Isp=310s. First flight 1985.
Application: R-29RM / RSM-54 (SS-N-23) stage 1.
Chamber Pressure: 275.00 bar. Area Ratio: 2. Oxidizer to Fuel Ratio: 2.6.
Status: Out of Production.
More... - Chronology...
Thrust: 682.00 kN (153,319 lbf).
Specific impulse: 310 s.
Specific impulse sea level: 280 s.
Burn time: 74 s.
First Launch: 1977-85.
Associated Launch Vehicles
R-29RM Russian submarine-launched ballistic missile. SLBM on Delta 4 subs. First flight June 1983. Developed 1973-1986. 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...
Vick, Charles, et al, KH-11 Photography of N1, Federation of American Scientists, 1995-present. Web Address when accessed: here.
Golubev, A A, KB KhimAvtomatiki - Straniy Istorii, Vol. 1, Voronezh 1995 via Dietrich Haeseler.
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.
R-29-1 N2O4/UDMH propellant rocket stage. Loaded mass 20,000 kg. Thrust 682.00 kN. More...
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