Lox/Kerosene propellant rocket stage. Loaded/empty mass 210,000/13,700 kg. Thrust 1,608.00 kN. Vacuum specific impulse 353 seconds.
No Engines: 4.
Status: Development ended 1974.
More... - Chronology...
Gross mass: 210,000 kg (460,000 lb).
Unfuelled mass: 13,700 kg (30,200 lb).
Height: 12.00 m (39.00 ft).
Diameter: 4.80 m (15.70 ft).
Span: 6.80 m (22.30 ft).
Thrust: 1,608.00 kN (361,492 lbf).
Specific impulse: 353 s.
Burn time: 370 s.
Number: 6 .
NK-39 Kuznetsov Lox/Kerosene rocket engine. 402 kN. N-1F stage 3. Development ended 1971. Isp=352s. Modified version of original engine with multiple ignition capability. Never flown and mothballed after the cancellation of the N1. More...
Associated Launch Vehicles
N1F Russian heavy-lift orbital launch vehicle. The N1F would have been the definitive flight version of the N1, incorporating all changes resulting from the four flight tests of the vehicle, including the new Kuznetsov engines and 10% greater liftoff mass by using superchilled propellants in all stages. N1 8L would have been the first N1F configuration flight, with launch planned in the third quarter of 1975 at the time the project was cancelled. More...
N1F Sr Russian heavy-lift orbital launch vehicle. The final more modest version of the N1F replaced the fourth and fifth stages of the N1 with the single liquid oxygen/liquid hydrogen Block Sr stage. Development of the Sr stage was from May 1971 until cancellation of the N1 project in May 1974. More...
N1F-L3M Russian heavy-lift orbital launch vehicle. The N1M was found to be too ambitious. The N1F of 1968 was instead pencilled in to be the first Soviet launch vehicle to use liquid oxygen/liquid hydrogen high energy cyrogenic propellants. The N1F would have only used the Block S and Block R fourth and fifth stages in place of the N1's Block G and Block D. 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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