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N-IMV-III
Part of N1 Family
N-IMV-III
N-IMV-III
Russian heavy-lift orbital launch vehicle. Then N-IMV-III would add the Block V-III cryogenic third stage to the first and second stages of the N-IM. This provided the second-highest performance of the variations considered and would certainly have been cheaper than the N-IFV-II, III.

Status: Study 1965. Payload: 185,000 kg (407,000 lb). Thrust: 74,000.00 kN (16,635,000 lbf). Gross mass: 4,950,000 kg (10,910,000 lb). Height: 145.00 m (475.00 ft). Diameter: 17.00 m (55.00 ft). Apogee: 220 km (130 mi).

LEO Payload: 185,000 kg (407,000 lb) to a 220 km orbit at 51.60 degrees.

Stage Data - N-IMV-III

  • Stage 1. 1 x N1M 1965 - A. Gross Mass: 3,800,000 kg (8,300,000 lb). Empty Mass: 375,000 kg (826,000 lb). Thrust (vac): 85,300.000 kN (19,176,200 lbf). Isp: 330 sec. Burn time: 130 sec. Isp(sl): 296 sec. Diameter: 10.00 m (32.00 ft). Span: 17.00 m (55.00 ft). Length: 50.00 m (164.00 ft). Propellants: Lox/Kerosene. No Engines: 30. Engine: 11D51M. Status: Study 1965. Comments: As per N1 improvement study, 1965. Huge modification of Block A, almost double propellant capacity, engines increased from 175 metric tons thrust to 250 metric tons.
  • Stage 2. 1 x N1M 1965 - B. Gross Mass: 620,000 kg (1,360,000 lb). Empty Mass: 75,000 kg (165,000 lb). Thrust (vac): 21,960.000 kN (4,936,800 lbf). Isp: 346 sec. Burn time: 85 sec. Diameter: 6.80 m (22.30 ft). Span: 9.80 m (32.10 ft). Length: 30.00 m (98.00 ft). Propellants: Lox/Kerosene. No Engines: 8. Engine: 11D52M. Status: Study 1965. Comments: As per N1 improvement study, 1965. Further stretch of Block B and thrust increased again to 280 metric tons per engine.
  • 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.



Family: heavy-lift, orbital launch vehicle. Country: Russia. Engines: RD-57, 11D51M, 11D52M. Stages: N1 Block V-III, N1M 1965 - A, N1M 1965 - B. Agency: Korolev bureau.

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