Korolev nuclear/LH2 rocket engine. 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.
Status: Study 1963. Thrust: 196.00 kN (44,062 lbf). Unfuelled mass: 3,250 kg (7,160 lb). Specific impulse: 950 s. Burn time: 700 s.
Engine: 3,250 kg (7,160 lb). Thrust to Weight Ratio: 6.15.