Lox/Kerosene propellant rocket stage. Loaded/empty mass 110,000/8,250 kg. Thrust 2,393.72 kN. Vacuum specific impulse 311 seconds. R-7 strap-ons increased in size dimensionally 50%, equipped with 6 engines from R-9. Boost nuclear thermal core stage to altitude before ignition of nuclear engine. Masses calculated based on vehicle total weight and performance.
No Engines: 6.
Status: Development ended 1949.
More... - Chronology...
Gross mass: 110,000 kg (240,000 lb).
Unfuelled mass: 8,250 kg (18,180 lb).
Height: 27.00 m (88.00 ft).
Diameter: 3.33 m (10.92 ft).
Span: 3.33 m (10.92 ft).
Thrust: 2,393.72 kN (538,131 lbf).
Specific impulse: 311 s.
Specific impulse sea level: 269 s.
Burn time: 125 s.
RD-111 Glushko Lox/Kerosene rocket engine. 1628 kN. R-9 stage 1. Isp=317s. Developed for R-9 ICBM. It had special flexible pipelines and gimbals, allowing lox loading in 20 minutes. First flight 1961. More...
Associated Launch Vehicles
YaKhR-2 Russian nuclear-powered orbital launch vehicle. First large space launcher considered in the Soviet Union. It would have had the same layout as the R-7, but with six strap-ons increased in size by 50%. The core, igniting at altitude, used a nuclear thermal engine using ammonia as propellant. Dropped in favor of development of conventional chemical propulsion. 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...
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