Encyclopedia Astronautica
PF RP-1


Notional Lox/Kerosene rocket engine. 20,306 kN. Study 1967. Isp=275s. Used on Saturn LCB-Lox/RP-1 launch vehicle.

Status: Study 1967.
Thrust: 20,306.00 kN (4,564,970 lbf).
Specific impulse: 275 s.
Specific impulse sea level: 253 s.
Burn time: 163 s.

More... - Chronology...


Associated Countries
See also
Associated Launch Vehicles
  • Saturn LCB-Lox/RP-1 American orbital launch vehicle. Boeing Low-Cost Saturn Derivative Study, 1967 (trade study of 260 inch first stages for S-IVB, all delivering 86,000 lb pyld to LEO): Low Cost Booster, Single Pressure-fed Lox/RFP-1 engine. More...

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
  • Saturn LCB-Lox/RP-1 Lox/Kerosene propellant rocket stage. Loaded/empty mass 1,360,800/108,900 kg. Thrust 20,306.60 kN. Vacuum specific impulse 275 seconds. Boeing Low-Cost Saturn Derivative Study, 1967 (trade study of 260 inch first stages for S-IVB, all delivering 86,000 lb pyld to LEO): Low Cost Booster, Single Pressure-fed Lox/RFP-1 engine More...

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