Encyclopedia Astronautica

Rocketdyne Lox/Kerosene rocket engine. 412.8 kN. Design ca. 1957. Version of Atlas sustainer tailored to Redstone Arsenal upper-stage requirements. Paper study only. Used on Super Jupiter launch vehicle.

Status: Design ca. 1957.
Thrust: 412.80 kN (92,801 lbf).
First Launch: 1957.

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Associated Countries
See also
Associated Launch Vehicles
  • Super-Jupiter American orbital launch vehicle. The very first design that would lead to Saturn. A 1.5 million pound thrust booster using four E-1 engines - initial consideration of using a single USAF F-1 engine abandoned because of development time. Existing missile tankage was clustered above the engines. 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...

Associated Stages
  • Super-Jupiter-3 Lox/Kerosene propellant rocket stage. Loaded/empty mass 29,400/1,900 kg. Thrust 412.80 kN. Vacuum specific impulse 308 seconds. Length estimated. More...

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