Lox/Kerosene propellant rocket stage. Loaded/empty mass 1,934,000/195,000 kg. Thrust 49,420.00 kN. Vacuum specific impulse 331 seconds. As per N1 improvement study, 1965. Primarily improved reliability and produceability compared to first model.
No Engines: 30.
Status: Study 1965.
More... - Chronology...
Gross mass: 1,934,000 kg (4,263,000 lb).
Unfuelled mass: 195,000 kg (429,000 lb).
Height: 30.00 m (98.00 ft).
Diameter: 10.00 m (32.00 ft).
Span: 17.00 m (55.00 ft).
Thrust: 49,420.00 kN (11,110,050 lbf).
Specific impulse: 331 s.
Specific impulse sea level: 296 s.
Burn time: 110 s.
NK-15 Kuznetsov Lox/Kerosene rocket engine. 1544 kN. N-1 stage 1 (block A). Development ended 1964. On the basis of NK-9 the NK-15 was developed for the N-1 launcher. 30 were used on the Block A (Stage 1) of the N-1. Isp=318s. First flight 1969. More...
Associated Launch Vehicles
N-IUV-III Russian heavy-lift orbital launch vehicle. The N-IUV-III would replace the N-IU's conventional third stage with a LOX/LH2 cryogenic third stage. This was seen at the time as the first step in exploitation of cryogenic technology in Russia. Although pursued for some time, this large stage never went into development. The more modestly-sized Block R, Block S, and Block SR instead were put into development in the early 1970's. More...
N-IU Russian heavy-lift orbital launch vehicle. The N-IU would be the initial production version of the N1 following the mad rush to make the lunar landings. It would have essentially the same payload but would be substantially re-engineered for sharply improved reliability, most notably with autonomously operating engines. It is interesting to note that four years before the disastorous first flight Korolev already foresaw the potential engine problems that would be the downfall of the project. 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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