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N1 Nuclear V
Part of N1
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.

Status: Study 1963. Payload: 420,000 kg (920,000 lb). Thrust: 35,000.00 kN (7,868,000 lbf). Gross mass: 2,600,000 kg (5,700,000 lb). Height: 190.00 m (620.00 ft). Diameter: 17.00 m (55.00 ft). Apogee: 220 km (130 mi).

LEO Payload: 420,000 kg (920,000 lb) to a 220 km orbit at 51.60 degrees. Payload: 38,500 kg (84,800 lb) to a lunar surface.

Stage Data - N1 Nuclear V



Subtopics

N1 Nuclear V stage Nuclear/LH2 propellant rocket stage. N1 nuclear upper stage study, 1963. Figures calculated based on given total stage thrust, specific impulse, engine mass.

N1 Nuclear V-Bioshield Nuclear/LH2 propellant rocket stage. N1 nuclear upper stage study, 1963. Figures calculated based on given total stage thrust, specific impulse, engine mass.

Family: nuclear-powered, orbital launch vehicle. Country: Russia. Engines: NK-15, YaRD Type V. Stages: N1 1962 - A, N1 Nuclear V stage. Agency: Korolev bureau.

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