Kuznetsov lox/lh2 rocket engine. 1960 kN. N-1 stage 2 (block B) replacement. Design 1972. Derivative of NK-15 with kerosene replaced by hydrogen. Canceled before hot-tests.
Derivative of NK-15 with kerosene replaced by hydrogen. Canceled before hot-tests. Intended for cryogenic second stage of N-IFV-II,III or N-IMV-II,III launcher versions studied in 1965.
Application: N-1 stage 2 (block B) replacement.
AKA: NK-35; NK-15VM; 11D52VM.
More... - Chronology...
Status: Design 1972.
Thrust: 1,960.00 kN (440,620 lbf).
First Launch: 1965.
Associated Launch Vehicles
N-IFV-II-III Russian heavy-lift orbital launch vehicle. N-IFV-II, III would use only the first stage from the N-1F, and use new cryogenic second and third stages. This cryogenic second stage seems not to have been pursued beyond the study phase. More...
N-IMV-II-III Russian heavy-lift orbital launch vehicle. N-IMV-II, III was the ultimate conventionally-powered N1 ever considered. It paired the monster N-1M first stage with new cryogenic second and third stages. Both liftoff thrust and payload of this vehicle would have been double that of the American Saturn V. More...
Associated Manufacturers and Agencies
Kuznetsov Russian manufacturer of rocket engines. Kuznetsov Design Bureau, Russia. More...
Lox/LH2 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. Liquid hydrogen was identified by all the leading rocket visionaries as the theoretically ideal rocket fuel. It had big drawbacks, however - it was highly cryogenic, and it had a very low density, making for large tanks. The United States mastered hydrogen technology for the highly classified Lockheed CL-400 Suntan reconnaissance aircraft in the mid-1950's. The technology was transferred to the Centaur rocket stage program, and by the mid-1960's the United States was flying the Centaur and Saturn upper stages using the fuel. It was adopted for the core of the space shuttle, and Centaur stages still fly today. More...
N1 Block V-II Lox/LH2 propellant rocket stage. Loaded/empty mass 805,000/115,000 kg. Thrust 7,840.00 kN. Vacuum specific impulse 440 seconds. N1 improvement study, 1965. Lox/LH2 replacement for Block B second stage. More...
UR-700M-3 Lox/LH2 propellant rocket stage. Loaded/empty mass 2,000,000/200,000 kg. Thrust 11,700.00 kN. Vacuum specific impulse 455 seconds. Total mass, length, estimated based on empty mass, total vehicle mass. Engine specific impulse estimated based on performance requirements. More...
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