Korolev nuclear/lh2 rocket engine. 392 kN. Study 1963. Design considered in N1 nuclear upper stage studies. Outgrowth of work done by Bondaryuk and Glushko on YaRD engines for nuclear ICBM's, but using liquid hydrogen as propellant. Isp=900s.
Application: nuclear ICBM.
Engine: 18,000 kg (39,000 lb). Thrust to Weight Ratio: 2.22.
Status: Study 1963.
More... - Chronology...
Unfuelled mass: 18,000 kg (39,000 lb).
Thrust: 392.00 kN (88,125 lbf).
Specific impulse: 900 s.
Burn time: 700 s.
Associated Launch Vehicles
N1 Nuclear V Russian nuclear orbital launch vehicle. Second primary alternative considered for the 1963 nuclear N1 study. The immense liquid hydrogen tank of the second nuclear stage would have dwarfed the N1 first stage mounted below it in the shadows. The extremely poor thrust to weight ratio of the Type V engine design compared to that of the Type A remains unexplained. More...
Associated Manufacturers and Agencies
Korolev Russian manufacturer of rockets, spacecraft, and rocket engines. Korolev Design Bureau, Kaliningrad, Russia. More...
Nuclear/LH2 Nuclear thermal engines use the heat of a nuclear reactor to heat a propellant. Although early Russian designs used ammonia or alcohol as propellant, the ideal working fluid for space applications is the liquid form of the lightest element, hydrogen. Nuclear engines would have twice the performance of conventional chemical rocket engines. Although successfully ground-tested in both Russia and America, they have never been flown due primarily to environmental and safety concerns. 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...
Vetrov, G S, S. P. Korolev i evo delo, Nauka, Moscow, 1998.
N1 Nuclear V Nuclear/LH2 propellant rocket stage. Loaded/empty mass 1,500,000/500,000 kg. Thrust 14,700.00 kN. Vacuum specific impulse 900 seconds. N1 nuclear upper stage study, 1963. Figures calculated based on given total stage thrust, specific impulse, engine mass. More...
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