Glushko Nitric acid/Kerosene rocket engine. 642.3 kN. long-distance missile. Developed 1952-55. Original four-chamber engine design planned for use on the R-12 IRBM. Abandoned due to limited thrust and the RD-214 was developed in its place. Isp=261s.
Application: long-distance missile.
Chambers: 4. Engine: 635 kg (1,400 lb). Chamber Pressure: 39.20 bar. Area Ratio: 9.52. Propellant Formulation: AK20/TM-185. Thrust to Weight Ratio: 103.11. Oxidizer to Fuel Ratio: 4.05.
Status: Developed 1952-55.
More... - Chronology...
Unfuelled mass: 635 kg (1,400 lb).
Height: 2.70 m (8.80 ft).
Diameter: 1.65 m (5.41 ft).
Thrust: 642.30 kN (144,395 lbf).
Specific impulse: 262 s.
Specific impulse sea level: 224 s.
Burn time: 122 s.
First Launch: 1952-55.
Associated Manufacturers and Agencies
Glushko Russian manufacturer of rocket engines and rockets. Glushko Design Bureau, Russia. More...
Nitric acid/Kerosene 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. Rocket propellant RP-1, or its foreign equivalents, is a straight-run kerosene fraction, which is subjected to further treatment, i.e., acid washing, sulphur dioxide extraction. Thus, unsaturated substances which polymerise in storage are removed, as are sulphur-containing hydrocarbons. More...
Glushko, V P, Albom Konstruktsiy ZhRD, Vol. 1 1968, Vol. 3 & 4 1969 via Dietrich Haeseler.
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