This page no longer updated from 31 October 2001. Latest version can be found at www.astronautix.com
Designer: Korolev. Application: nuclear ICBM. Used on stages: N1 Nuclear A. Used on launch vehicles: N1 Nuclear A. Propellants: Nuclear/LH2 Thrust(vac): 18,000 kgf. Thrust(vac): 177.00 kN. Isp: 900 sec. Burn time: 700 sec. Mass Engine: 4,800 kg. Chambers: 1. Country: Russia. Status: Study 1963. References: 283 . Comments: 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.
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Last update 12 March 2001.
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© Mark Wade, 2001 .