Encyclopedia Astronautica
N1F 1965 - A

Lox/Kerosene propellant rocket stage. Loaded/empty mass 1,940,000/200,000 kg. Thrust 57,560.00 kN. Vacuum specific impulse 331 seconds. As per N1 improvement study, 1965. Block A engine thrust increased but little additional propellant.

No Engines: 30.

Status: Study 1965.
Gross mass: 1,940,000 kg (4,270,000 lb).
Unfuelled mass: 200,000 kg (440,000 lb).
Height: 30.00 m (98.00 ft).
Diameter: 10.00 m (32.00 ft).
Span: 17.00 m (55.00 ft).
Thrust: 57,560.00 kN (12,940,000 lbf).
Specific impulse: 331 s.
Specific impulse sea level: 296 s.
Burn time: 100 s.

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Associated Countries
Associated Engines
  • 11D51F Kuznetsov Lox/Kerosene rocket engine. 1918 kN. N1F 1965 - A. Study 1965. As described in N1 improvement study, 1965. Block A engine thrust increased. Isp=331s. More...

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...
  • N-IFV-III Russian heavy-lift orbital launch vehicle. Then N-IFV-III would add the Block V-III cryogenic third stage to the first and second stages of the N-IF. More...
  • N-IFV-II-III Russian heavy-lift orbital launch vehicle. N-IFV-II, III would use only the first stage from the N-1F, and use new cryogenic second and third stages. This cryogenic second stage seems not to have been pursued beyond the study phase. 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...

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