Kosberg Lox/Kerosene rocket engine. 304 kN. R-9 stage 2. Gas generator cycle. Isp=330s. First flight 1961.
Application: R-9 stage 2.
Chambers: 4. Propellant Formulation: Lox/T-1.
More... - Chronology...
Thrust: 304.00 kN (68,341 lbf).
Specific impulse: 330 s.
Burn time: 140 s.
First Launch: 1959-62.
Number: 69 .
Associated Launch Vehicles
R-9 Russian intercontinental ballistic missile. ICBM developed by Korolev OKB using liquid oxygen/kerosene propellants. The Soviet military favoured storable propellants as advocated by Glushko and implemented by Yangel and Chelomei. Development of the R-9 was protracted and it was deployed in only very limited numbers between 1964 and 1974. More...
Associated Manufacturers and Agencies
Kosberg Russian manufacturer of rocket engines. Kosberg 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...
Russian Arms Catalogue, Vol 5 and 6, Military Parade, Moscow via Dietrich Haeseler.
R-9A Stage 2 Lox/Kerosene propellant rocket stage. Loaded/empty mass 15,900/2,500 kg. Thrust 304.00 kN. Vacuum specific impulse 330 seconds. Empty mass estimated. Developed into Molniya/Soyuz second stage. More...
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