Glushko Lox/Kerosene rocket engine. 19.9 kN. Design concept 1990's. Proposed for use on Soyuz M-3. Version with uncooled nozzle extension. Engine Cycle: closed gas generator. Feed Method: turbopump. Isp=365s.
Engine: 141 kg (310 lb). Chamber Pressure: 117.70 bar. Area Ratio: 370.6. Thrust to Weight Ratio: 14.39. Oxidizer to Fuel Ratio: 2.6.
Status: Design concept 1990's.
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Unfuelled mass: 141 kg (310 lb).
Height: 2.21 m (7.25 ft).
Diameter: 1.02 m (3.34 ft).
Thrust: 19.90 kN (4,474 lbf).
Specific impulse: 365 s.
Burn time: 900 s.
Associated Manufacturers and Agencies
Glushko Russian manufacturer of rocket engines and rockets. Glushko Design Bureau, Russia. More...
Lox/Kerosene 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. In January 1953 Rocketdyne commenced the REAP program to develop a number of improvements to the engines being developed for the Navaho and Atlas missiles. Among these was development of a special grade of kerosene suitable for rocket engines. Prior to that any number of rocket propellants derived from petroleum had been used. Goddard had begun with gasoline, and there were experimental engines powered by kerosene, diesel oil, paint thinner, or jet fuel kerosene JP-4 or JP-5. The wide variance in physical properties among fuels of the same class led to the identification of narrow-range petroleum fractions, embodied in 1954 in the standard US kerosene rocket fuel RP-1, covered by Military Specification MIL-R-25576. In Russia, similar specifications were developed for kerosene under the specifications T-1 and RG-1. The Russians also developed a compound of unknown formulation in the 1980's known as 'Sintin', or synthetic kerosene. More...
Haeseler, Dietrich, NPO Energomash exhibit at Moscow Airshow MAKS 93, Moscow, 1993 via Dietrich Haeseler.
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