Lox/Kerosene propellant rocket stage. Loaded/empty mass 193,000/16,000 kg. Thrust 1,560.00 kN. Vacuum specific impulse 347 seconds. As per draft project for N1-L3, 1964. Thrust said to be increased 2% but not reflected in figures given.
No Engines: 4.
Status: Development ended 1964.
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Gross mass: 193,000 kg (425,000 lb).
Unfuelled mass: 16,000 kg (35,000 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: 368 s.
Number: 4 .
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
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...
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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