Lox/Alcohol propellant rocket stage. Loaded/empty mass 27,250/3,250 kg. Thrust 479.22 kN. Vacuum specific impulse 244 seconds.
Propellant Formulation: Lox/92% Ethyl alcohol.
More... - Chronology...
Status: Retired 1983.
Gross mass: 27,250 kg (60,070 lb).
Unfuelled mass: 3,250 kg (7,160 lb).
Height: 20.75 m (68.07 ft).
Diameter: 1.65 m (5.42 ft).
Span: 2.64 m (8.66 ft).
Thrust: 479.22 kN (107,733 lbf).
Specific impulse: 244 s.
Specific impulse sea level: 219 s.
Burn time: 112 s.
Number: 188 .
RD-103M Glushko Lox/Alcohol rocket engine. 500.1 kN. R-5M 8K51. Isp=248s. First flight 1953. More...
Associated Launch Vehicles
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R-5B Russian intermediate range ballistic missile. More...
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Lox/Alcohol 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. Alcohol (C2H5OH) was the fuel used for the German V-2 rocket, and the first derivative rocket engines in the United States, Soviet Union, and China used it as well. Better performance was achieved by increasing the alcohol concentration in the post-war engines. But after better-performance rocket-grade kerosene was developed by Rocketdyne in the REAP program of 1953, use of alcohol was abandoned. More...
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