Encyclopedia Astronautica

Glushko lox/udmh rocket engine. 1653 kN. Used in ICBM stage 1 (stage 2 was RD-115). Developed 1961-65. Isp=341s.

Application: Used in ICBM stage 1 (stage 2 was RD-115).

Engine: 990 kg (2,180 lb). Chamber Pressure: 147.00 bar. Area Ratio: 26.4. Thrust to Weight Ratio: 170.26. Oxidizer to Fuel Ratio: 1.77.

Status: Developed 1961-65.
Unfuelled mass: 990 kg (2,180 lb).
Height: 2.60 m (8.50 ft).
Diameter: 1.46 m (4.80 ft).
Thrust: 1,653.00 kN (371,609 lbf).
Specific impulse: 341 s.
Specific impulse sea level: 307 s.
Burn time: 120 s.
First Launch: 1961-65.

More... - Chronology...

Associated Countries
See also
Associated Manufacturers and Agencies
  • Glushko Russian manufacturer of rocket engines and rockets. Glushko Design Bureau, Russia. More...

Associated Propellants
  • Lox/UDMH Liquid oxygen was the earliest, cheapest, safest, and eventually the preferred oxidiser for large space launchers. Its main drawback is that it is moderately cryogenic, and therefore not suitable for military uses where storage of the fuelled missile and quick launch are required. 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...

  • Glushko, V P, Albom Konstruktsiy ZhRD, Vol. 1 1968, Vol. 3 & 4 1969 via Dietrich Haeseler.

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