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N1 Nuclear AF

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Status: Study 1963. Payload: 300,000 kg (660,000 lb). Thrust: 35,000.00 kN (7,868,000 lbf). Gross mass: 2,500,000 kg (5,500,000 lb). Height: 200.00 m (650.00 ft). Diameter: 17.00 m (55.00 ft). Apogee: 220 km (130 mi).

LEO Payload: 300,000 kg (660,000 lb) to a 220 km orbit at 51.60 degrees. Payload: 27,100 kg (59,700 lb) to a lunar surface.

Stage Data - N1 Nuclear AF

• 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 AF. Gross Mass: 800,000 kg (1,760,000 lb). Empty Mass: 150,000 kg (330,000 lb). Thrust (vac): 7,840.000 kN (1,762,500 lbf). Isp: 810 sec. Burn time: 650 sec. Diameter: 13.00 m (42.00 ft). Span: 13.00 m (42.00 ft). Length: 110.00 m (360.00 ft). Propellants: Nuclear/LH2. No Engines: 40. Engine: YaRD Type AF. Status: Study 1963. Comments: N1 nuclear upper stage study, 1963. Figures calculated based on given total stage thrust, specific impulse, engine mass.