Lox/Kerosene propellant rocket stage. Loaded/empty mass 100,600/6,798 kg. Thrust 976.70 kN. Vacuum specific impulse 315 seconds.
Cost $ : 13.000 million.
More... - Chronology...
Gross mass: 100,600 kg (221,700 lb).
Unfuelled mass: 6,798 kg (14,987 lb).
Height: 28.00 m (91.00 ft).
Diameter: 2.99 m (9.80 ft).
Span: 2.60 m (8.50 ft).
Thrust: 976.70 kN (219,571 lbf).
Specific impulse: 315 s.
Specific impulse sea level: 248 s.
Burn time: 291 s.
Number: 1067 .
RD-108-8D727 Glushko Lox/Kerosene rocket engine. 977 kN. Molniya 1, Molniya 8K78M-1. OKB Glushko. Used on Molniya 8K78L, 8K78M and 11A57 Stage 1. Propellants kerosene (RG-1 or T-1) / Lox. Diameter is per chamber. Isp=316s. 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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