Encyclopedia Astronautica
N1 1964 - A



8dmaiun3.jpg
NK-15 / 11D51
NK-15 / 11D51 rocket engine for first stage of N1
Credit: © Mark Wade
Lox/Kerosene propellant rocket stage. Loaded/empty mass 1,942,000/192,000 kg. Thrust 49,420.00 kN. Vacuum specific impulse 331 seconds. First stage of the N1 superbooster. As per draft project for N1-L3, 1964. Block A modified with six additional engines and propellant increased by 550 tonnes by using chilled propellants.

No Engines: 30.

Status: Development ended 1964.
Gross mass: 1,942,000 kg (4,281,000 lb).
Unfuelled mass: 192,000 kg (423,000 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: 113 s.
Number: 4 .

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Associated Countries
Associated Engines
  • 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
  • N1 1964 Russian heavy-lift orbital launch vehicle. The N1 launch vehicle for the N1-L3 lunar landing mission as described in the draft project of 1964. Design requirement for the single-launch lunar-orbit-rendezvous lunar landing was 2750 tonnes liftoff mass and 95 tonnes low earth orbit payload. The actual N1 that flew in 1969 to 1972 had lighter first and third stages, but never demonstrated a full fuel load using superchilled propellants as planned in the draft 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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