Encyclopedia Astronautica

Credit: © Mark Wade
Rocketdyne Lox/Kerosene rocket engine. 760.6 kN. Out of production. Designed for booster applications. Gas generator, pump-fed. Isp=285s. Boosted Delta A, B, C, Thor Able-Star. First flight 1960.

Thrust (sl): 667.200 kN (149,993 lbf). Thrust (sl): 68,039 kgf. Engine: 643 kg (1,417 lb). Chamber Pressure: 40.00 bar. Area Ratio: 8. Propellant Formulation: Lox/RP-1. Thrust to Weight Ratio: 120.628304821151. Coefficient of Thrust vacuum: 1.39705131752785. Coefficient of Thrust sea level: 1.19705131752785.

Status: Out of production.
Unfuelled mass: 643 kg (1,417 lb).
Diameter: 2.44 m (8.00 ft).
Thrust: 760.60 kN (170,990 lbf).
Specific impulse: 285 s.
Specific impulse sea level: 250 s.
Burn time: 164 s.
First Launch: 1957.
Number: 43 .

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Associated Countries
See also
Associated Launch Vehicles
  • Thor Able-Star American orbital launch vehicle. As Thor Able but with enlarged Ablestar second stage with 2 1/2 x greater burn time. More...
  • Delta A American orbital launch vehicle. Three stage vehicle consisting of 1 x Thor DM-21 + 1 x AJ10-118 + 1 x Altair More...
  • Delta B American orbital launch vehicle. Three stage vehicle consisting of 1 x Thor DM-21 + 1 x AJ10-118A + 1 x Altair More...
  • Delta C American orbital launch vehicle. Unaugmented Thor with Delta D and solid propellant upper stages. 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
  • Thor DM-21 Lox/Kerosene propellant rocket stage. Loaded/empty mass 48,354/2,948 kg. Thrust 760.64 kN. Vacuum specific impulse 285 seconds. More...

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