Encyclopedia Astronautica

Credit: Boeing / Rocketdyne
E-1 Engine
Credit: © Mark Wade
Rocketdyne Lox/Kerosene rocket engine. 1885 kN. Study 1957. Developed by USAF in late 1950's. Cancelled and decision to go direct to 1,500,000 lbf F-1 as next step. Booster applications. Gas generator, pump-fed. Isp=290s.

Thrust (sl): 1,689.600 kN (379,837 lbf). Thrust (sl): 172,300 kgf. Propellant Formulation: Lox/RP-1.

Status: Study 1957.
Thrust: 1,884.59 kN (423,673 lbf).
Specific impulse: 290 s.
Specific impulse sea level: 260 s.
First Launch: 1957.

More... - Chronology...

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 Lox/Kerosene propellant rocket stage. Loaded/empty mass 317,600/19,600 kg. Thrust 7,538.30 kN. Vacuum specific impulse 290 seconds. Earliest member of what would become the Saturn family. Masses estimated. More...
  • Super-Jupiter-2 Lox/Kerosene propellant rocket stage. Loaded/empty mass 96,700/7,200 kg. Thrust 1,884.59 kN. Vacuum specific impulse 290 seconds. More...

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