Glushko Nitric acid/UDMH rocket engine. 864 kN. R-14, Kosmos 11K63 stage 1. Out of Production. Original intended use unknown. Two RD-215 clustered to make RD-216. Isp=291s. First flight 1966.
Application: R-14, Kosmos 11K63 stage 1.
Chambers: 2. Engine: 675 kg (1,488 lb). Chamber Pressure: 73.60 bar. Area Ratio: 18.8. Propellant Formulation: RFNA/UDMH. Thrust to Weight Ratio: 130.51. Oxidizer to Fuel Ratio: 2.5.
Status: Out of Production.
More... - Chronology...
Unfuelled mass: 675 kg (1,488 lb).
Thrust: 864.00 kN (194,234 lbf).
Specific impulse: 291 s.
Specific impulse sea level: 248 s.
Burn time: 146 s.
First Launch: 1958-60.
Associated Manufacturers and Agencies
Glushko Russian manufacturer of rocket engines and rockets. Glushko Design Bureau, Russia. More...
Nitric acid/UDMH Drawing on the German World War II Wasserfall rocket, nitric acid (HNO3) became the early storable oxidiser of choice for missiles and upper stages of the 1950's. To overcome various problems with its use, it was necessary to combine the nitric acid with N2O4 and passivation compounds. These formulae were considered extremely secret at the time. By the late 1950's it was apparent that N2O4 by itself was a better oxidiser. Therefore nitric acid was almost entirely replaced by pure N2O4 in storable liquid fuel rocket engines developed after 1960. 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.
Kosmos A-1 Nitric acid/Kerosene propellant rocket stage. Loaded/empty mass 39,515/3,150 kg. Thrust 730.50 kN. Vacuum specific impulse 264 seconds. More...
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