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N1 Nuclear V

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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

• Stage 1. 1 x N1 1962 - A. Gross Mass: 1,384,000 kg (3,051,000 lb). Empty Mass: 117,000 kg (257,000 lb). Thrust (vac): 39,420.000 kN (8,861,960 lbf). Isp: 331 sec. Burn time: 103 sec. Isp(sl): 296 sec. Diameter: 10.00 m (32.00 ft). Span: 17.00 m (55.00 ft). Length: 30.00 m (98.00 ft). Propellants: Lox/Kerosene. No Engines: 24. Engine: NK-15. Status: Study 1962. Comments: Includes 14,000 kg for Stage 1-2 interstage and payload fairing. Compared to total fuelled mass excludes 15,000 kg propellant expended in thrust build-up and boil-off prior to liftoff. Values as in draft project as defended on 2-16 July 1962.

• Stage 2. 1 x N1 Nuclear V. Gross Mass: 1,500,000 kg (3,300,000 lb). Empty Mass: 500,000 kg (1,100,000 lb). Thrust (vac): 14,700.000 kN (3,304,600 lbf). Isp: 900 sec. Burn time: 590 sec. Diameter: 17.00 m (55.00 ft). Span: 17.00 m (55.00 ft). Length: 100.00 m (320.00 ft). Propellants: Nuclear/LH2. No Engines: 20. Engine: YaRD Type V. Status: Study 1963. Comments: N1 nuclear upper stage study, 1963. Figures calculated based on given total stage thrust, specific impulse, engine mass.