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N-IFV-III

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N1FV-III N-IFV-III design of 1965

Status: Study 1965. Payload: 125,000 kg (275,000 lb). Thrust: 51,500.00 kN (11,577,600 lbf). Gross mass: 3,000,000 kg (6,600,000 lb). Height: 125.00 m (410.00 ft). Diameter: 17.00 m (55.00 ft). Apogee: 220 km (130 mi).

LEO Payload: 125,000 kg (275,000 lb) to a 220 km orbit at 51.60 degrees.

Stage Data - N-IFV-III

• Stage 1. 1 x N1F 1965 - A. Gross Mass: 1,940,000 kg (4,270,000 lb). Empty Mass: 200,000 kg (440,000 lb). Thrust (vac): 57,560.000 kN (12,940,000 lbf). Isp: 331 sec. Burn time: 100 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: 30. Engine: 11D51F. Status: Study 1965. Comments: As per N1 improvement study, 1965. Block A engine thrust increased but little additional propellant.

• Stage 2. 1 x N1F 1965 - B. Gross Mass: 590,000 kg (1,300,000 lb). Empty Mass: 60,000 kg (132,000 lb). Thrust (vac): 15,600.000 kN (3,507,000 lbf). Isp: 346 sec. Burn time: 115 sec. Diameter: 6.80 m (22.30 ft). Span: 9.80 m (32.10 ft). Length: 26.00 m (85.00 ft). Propellants: Lox/Kerosene. No Engines: 8. Engine: 11D52F. Status: Study 1965. Comments: As per N1 improvement study, 1965. Engine thrust increased from 150 t each to 200 t and stretched propellant tanks.

• Stage 3. 1 x N1 Block V-III. Gross Mass: 325,000 kg (716,000 lb). Empty Mass: 35,000 kg (77,000 lb). Thrust (vac): 2,350.000 kN (528,300 lbf). Isp: 440 sec. Burn time: 510 sec. Diameter: 8.00 m (26.20 ft). Span: 8.00 m (26.20 ft). Length: 27.00 m (88.00 ft). Propellants: Lox/LH2. No Engines: 6. Engine: RD-57. Status: Study 1965. Comments: N1 improvement study, 1965. Lox/LH2 replacement for Block V third stage. Pursued into 1966 and later, but later efforts concentrated on Block S, R, and SR cryogenic stages.