Encyclopedia Astronautica

Credit: Boeing / Rocketdyne
Rocketdyne Lox/Kerosene rocket engine. Launch thrust 600.1 kN. Jupiter Booster. Gas generator, pump-fed. Thrust later 150,000 lbs. Thrust and specific impulse values are at sea level. First flight 1957.

Thrust (sl): 600.100 kN (134,908 lbf). Thrust (sl): 61,200 kgf. Propellant Formulation: Lox/RP-1.

Thrust: 600.10 kN (134,908 lbf).
Specific impulse: 247 s.
Specific impulse sea level: 247 s.
First Launch: 1955.

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Associated Countries
See also
Associated Launch Vehicles
  • Jupiter American intermediate range ballistic missile. The Jupiter IRBM was developed for the US Army. By the time development was complete, the mission and the missile was assigned to the US Air Force, which had its own nearly identical missile, the Thor. Jupiters were stationed in Turkey and Italy in the early 1960's, but withdrawn in secret exchange for the withdrawal of Soviet R-5 missiles from Cuba. The Jupiter was used as the first stage of the relatively unsuccessful Juno II launch vehicle, and proposed for the Juno III and Juno IV. Jupiter tooling and engines were used to build the much larger Juno V / Saturn I launch vehicle. More...

Associated Manufacturers and Agencies
Associated Propellants
  • 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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