Encyclopedia Astronautica
11D53F


Kuznetsov Lox/Kerosene rocket engine. 612 kN. N1F 1965 - V. Study 1965. As per N1 improvement study, 1965. Engine thrust increased and stretched propellant tanks resulting in 20% longer burn time. Isp=346s.

Application: N1F 1965 - V.

Status: Study 1965.
Thrust: 612.00 kN (137,583 lbf).
Specific impulse: 346 s.
First Launch: 1965.

More... - Chronology...


Associated Countries
See also
Associated Launch Vehicles
  • N-IF 1965 Russian heavy-lift orbital launch vehicle. The N-IF would be the first follow-on version with increased performance. The first stage engines would be increased in thrust from an average of 150 tonnes to 175 tonnes, and those in the second stage from 150 tonnes to 200 tonnes. The second and third stages would be substantially 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...

Bibliography
  • Vetrov, G S, S. P. Korolev i evo delo, Nauka, Moscow, 1998.
  • Anisimov, V S; Lacefield, T C; Andrews, J, "Evolution of the NK-33 and NK-43 reusable LOX/kerosene engines", AIAA Joint Propulsion Conference, via Dietrich Haeseler.
  • Russian Space Industry, Federation of American Scentists Web Pages, 1998 via Dietrich Haeseler. Web Address when accessed: here.

Associated Stages
  • N1F 1965 - V Lox/Kerosene propellant rocket stage. Loaded/empty mass 300,000/20,000 kg. Thrust 2,450.00 kN. Vacuum specific impulse 347 seconds. As per N1 improvement study, 1965. Engine thrust increased and stretched propellant tanks with almost 50% increase. More...

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