Encyclopedia Astronautica
RD-108-8D75-1959


Glushko Lox/Kerosene rocket engine. 941 kN. Out of production. Further development of 8D74-1958, 1958-1959. Diameter is per chamber. Isp=315s. Used on Vostok 8K72K launch vehicle. First flight 1960.

Chambers: 4. Engine: 1,250 kg (2,750 lb). Chamber Pressure: 51.00 bar. Area Ratio: 18.9. Thrust to Weight Ratio: 76.8. Oxidizer to Fuel Ratio: 2.39.

AKA: 8D75-1959.
Status: Out of production.
Unfuelled mass: 1,250 kg (2,750 lb).
Height: 2.86 m (9.38 ft).
Diameter: 0.67 m (2.19 ft).
Thrust: 941.00 kN (211,545 lbf).
Specific impulse: 315 s.
Specific impulse sea level: 248 s.
Burn time: 340 s.
Number: 13 .

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Associated Countries
See also
Associated Launch Vehicles
  • Vostok 8K72K Russian orbital launch vehicle. R-7 ICBM with single-engine third stage, uprated from Luna launch vehicle and with forward fairing to accomodate Vostok/Zenit sized spacecraft. 8K72K, used for Vostok manned spacecraft launches and the first Zenit launch attempt. More...

Associated Manufacturers and Agencies
  • Glushko Russian manufacturer of rocket engines and rockets. Glushko Design Bureau, Russia. 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
  • Vostok 8K72K-1 Lox/Kerosene propellant rocket stage. Loaded/empty mass 100,400/6,800 kg. Thrust 912.00 kN. Vacuum specific impulse 315 seconds. More...

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