Encyclopedia Astronautica

Kuznetsov Lox/Kerosene rocket engine. 735 kN. N1M 1965 - V. Study 1965. As per N1 improvement study, 1965. Further increase in thrust of Block V engines. Isp=347s. Used on N-IM 1965 launch vehicle.

Application: N1M 1965 - V.

Status: Study 1965.
Thrust: 735.00 kN (165,234 lbf).
Specific impulse: 347 s.
First Launch: 1965.

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Associated Countries
See also
Associated Launch Vehicles
  • N-IM 1965 Russian heavy-lift orbital launch vehicle. The N-IM would mark an tremendous increase in vehicle size and was the ultimate pure liquid oxygen/kerosene version considered. The first stage engines would be increased to 250 tonnes thrust, without reducing reliability, through use of higher engine chamber pressure. Propellant load in the first stage would be almost doubled. Second stage engine thrust would increase to 280 tonnes each and the second and third stages again enlarged. More...

Associated Manufacturers and Agencies
  • Kuznetsov Russian manufacturer of rocket engines. Kuznetsov 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
  • N1M 1965 - V Lox/Kerosene propellant rocket stage. Loaded/empty mass 355,000/20,000 kg. Thrust 2,940.00 kN. Vacuum specific impulse 347 seconds. As per N1 improvement study, 1965. Further stretch of Block V. More...

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