Lox/Kerosene propellant rocket stage. Loaded/empty mass 43,400/3,770 kg. Thrust 995.30 kN. Vacuum specific impulse 314 seconds.
Cost $ : 5.000 million.
More... - Chronology...
Gross mass: 43,400 kg (95,600 lb).
Unfuelled mass: 3,770 kg (8,310 lb).
Height: 19.00 m (62.00 ft).
Diameter: 2.68 m (8.79 ft).
Span: 2.68 m (8.79 ft).
Thrust: 995.30 kN (223,752 lbf).
Specific impulse: 314 s.
Specific impulse sea level: 257 s.
Burn time: 119 s.
Number: 4268 .
RD-107-8D728 Glushko Lox/Kerosene rocket engine. 996 kN. Molniya 0, Molniya 8K78M-0. OKB Glushko. Used on Molniya 8K78M and 11A57 Stage 0. Propellants kerosene (RG-1 or T-1) / Lox. Diameter is per chamber. Isp=314s. First flight 1964. More...
Associated Launch Vehicles
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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...
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