Encyclopedia Astronautica
LR89-7



ma5rdyne.jpg
MA-5
Credit: Boeing / Rocketdyne
Rocketdyne Lox/Kerosene rocket engine. 948 kN. Atlas space launchers. Out of production. Designed for booster applications. Gas generator, pump-fed. Shared turbopumps for booster engines. Evolved from MA-2 ICBM system. Isp=294s. First flight 1963.

Application: Atlas space launchers..

Thrust (sl): 835.100 kN (187,738 lbf). Thrust (sl): 85,162 kgf. Engine: 712 kg (1,569 lb). Chamber Pressure: 42.00 bar. Area Ratio: 8. Propellant Formulation: Lox/RP-1. Thrust to Weight Ratio: 135.867884750527. Oxidizer to Fuel Ratio: 2.25. Coefficient of Thrust vacuum: 1.53013234508252. Coefficient of Thrust sea level: 1.34831416326433.

Status: Out of production.
Height: 3.40 m (11.10 ft).
Diameter: 1.53 m (5.00 ft).
Thrust: 948.00 kN (213,118 lbf).
Specific impulse: 294 s.
Specific impulse sea level: 259 s.
Burn time: 174 s.
First Launch: 1960.
Number: 198 .

More... - Chronology...


Associated Countries
See also
Associated Launch Vehicles
  • Atlas Agena D American orbital launch vehicle. Atlas D with further improved and lightened Agena upper stage. More...
  • Atlas H American orbital launch vehicle. Atlas H used the Atlas first stage developed for the Atlas G vehicle. It was flown without the Centaur upper stage. More...
  • Atlas I American orbital launch vehicle. The Atlas I launch vehicle was derived from the Atlas G, and included the same basic vehicle components (Atlas booster and Centaur upper stage). Significant improvements in the guidance and control system were made with an emphasis on replacing analog flight control components with digital units interconnected with a digital data bus. 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
  • Atlas MA-5 Lox/Kerosene propellant rocket stage. Loaded/empty mass 3,646/3,646 kg. Thrust 1,896.01 kN. Vacuum specific impulse 294 seconds. More...

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