Encyclopedia Astronautica

Credit: KBKhA
Kosberg N2O4/UDMH rocket engine. 825.8 kN. R-29RM stage 1. Out of Production. Isp=300s. Consisted pf single-chamber main engine RD-0244 plus four-chamber steering engines RD-0245 driven by turbine exhaust gas. Engine submerged in propellant tank.

Application: R-29RM / RSM-54 (SS-N-23) stage 1.

Chambers: 1 + 4. Engine: 853 kg (1,880 lb). Thrust to Weight Ratio: 98.73.

Status: Out of Production.
Unfuelled mass: 853 kg (1,880 lb).
Height: 1.90 m (6.20 ft).
Diameter: 2.27 m (7.44 ft).
Thrust: 825.80 kN (185,647 lbf).
Specific impulse: 300 s.
Burn time: 79 s.
First Launch: 1977-85.

More... - Chronology...

Associated Countries
See also
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...

Associated Propellants
  • 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.

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