Lox/Kerosene propellant rocket stage. Loaded/empty mass 3,800,000/375,000 kg. Thrust 85,300.00 kN. Vacuum specific impulse 330 seconds. As per N1 improvement study, 1965. Huge modification of Block A, almost double propellant capacity, engines increased from 175 tonnes thrust to 250 tonnes.
No Engines: 30.
Status: Study 1965.
More... - Chronology...
Gross mass: 3,800,000 kg (8,300,000 lb).
Unfuelled mass: 375,000 kg (826,000 lb).
Height: 50.00 m (164.00 ft).
Diameter: 10.00 m (32.00 ft).
Span: 17.00 m (55.00 ft).
Thrust: 85,300.00 kN (19,176,200 lbf).
Specific impulse: 330 s.
Specific impulse sea level: 296 s.
Burn time: 130 s.
11D51M Kuznetsov Lox/Kerosene rocket engine. 2843 kN. N1M 1965 - A. Study 1965. As described in N1 improvement study, 1965. Huge modification of Block A engines - sea level thrust increased from 175 tonnes thrust to 250 tonnes. Isp=346s. More...
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...
N-IMV-II-III Russian heavy-lift orbital launch vehicle. N-IMV-II, III was the ultimate conventionally-powered N1 ever considered. It paired the monster N-1M first stage with new cryogenic second and third stages. Both liftoff thrust and payload of this vehicle would have been double that of the American Saturn V. More...
N-IMV-III Russian heavy-lift orbital launch vehicle. Then N-IMV-III would add the Block V-III cryogenic third stage to the first and second stages of the N-IM. This provided the second-highest performance of the variations considered and would certainly have been cheaper than the N-IFV-II, III. More...
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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