YaRD Type V

Designer: Korolev. Application: nuclear ICBM. Propellants: Nuclear/LH2. Thrust(vac): 392.000 kN (88,125 lbf). Isp: 900 sec. Burn time: 700 sec. Mass Engine: 18,000 kg (39,000 lb). Chambers: 1. Thrust to Weight Ratio: 2.22. Country: Russia. Status: 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.

YaRD Type V used on Rocket Stages

Used on stage: N1 Nuclear V. on launch vehicle: N1 Nuclear V.

Bibliography and Further Reading

Vetrov, G S, S. P. Korolev i evo delo, Nauka, Moscow, 1998. ISBN: 5020036846. The collected papers of Soviet Chief Designer Korolev. A tremendous source of new information and insight on the Soviet space program. Russian language. More at amazon.com...

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