Encyclopedia Astronautica
N1U 1965 - V


Lox/Kerosene propellant rocket stage. Loaded/empty mass 193,000/15,000 kg. Thrust 1,560.00 kN. Vacuum specific impulse 347 seconds. As per N1 improvement study, 1965. Primarily improved reliability and produceability compared to first model.

No Engines: 4.

Status: Study 1965.
Gross mass: 193,000 kg (425,000 lb).
Unfuelled mass: 15,000 kg (33,000 lb).
Height: 12.00 m (39.00 ft).
Diameter: 4.80 m (15.70 ft).
Span: 6.80 m (22.30 ft).
Thrust: 1,560.00 kN (350,700 lbf).
Specific impulse: 347 s.
Burn time: 380 s.

More... - Chronology...


Associated Countries
Associated Engines
  • NK-19 Kuznetsov Lox/Kerosene rocket engine. N-1 stage 4. Development ended 1964. Based on NK-9 engine. Originally developed for the modernized second stage of the R-9 (abandoned). Also to have been used on GR-1 / 8K713 Stage 2. First flight 1969. More...

Associated Launch Vehicles
  • 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...

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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