Glushko lox/udmh rocket engine. 1726 kN. ICBM stage 2 (stage 1 was RD-114). Developed 1961-65. Upper stage version of RD-114 with larger nozzle. Isp=357s.
Application: ICBM stage 2 (stage 1 was RD-114).
Engine: 1,250 kg (2,750 lb). Chamber Pressure: 147.00 bar. Area Ratio: 86.2. Thrust to Weight Ratio: 140.8. Oxidizer to Fuel Ratio: 1.77.
Status: Developed 1961-65.
More... - Chronology...
Unfuelled mass: 1,250 kg (2,750 lb).
Height: 5.00 m (16.40 ft).
Diameter: 3.27 m (10.71 ft).
Thrust: 1,726.00 kN (388,020 lbf).
Specific impulse: 357 s.
Burn time: 130 s.
First Launch: 1961-65.
Associated Manufacturers and Agencies
Glushko Russian manufacturer of rocket engines and rockets. Glushko Design Bureau, Russia. More...
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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