N-IM 1965

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N-IM 1965

Part of N1

N-IM 1965
N-IM version of 1965

Russian heavy-lift orbital launch vehicle. The N-IM would mark an tremendous increase in vehicle size and was the ultimate pure liquid oxygen/kerosene version considered. The first stage engines would be increased to 250 metric tons thrust, without reducing reliability, through use of higher engine chamber pressure. Propellant load in the first stage would be almost doubled. Second stage engine thrust would increase to 280 metric tons each and the second and third stages again enlarged.

Status: Study 1965. Payload: 155,000 kg (341,000 lb). Thrust: 74,000.00 kN (16,635,000 lbf). Gross mass: 4,950,000 kg (10,910,000 lb). Height: 135.00 m (442.00 ft). Diameter: 17.00 m (55.00 ft). Apogee: 220 km (130 mi).

LEO Payload: 155,000 kg (341,000 lb) to a 220 km orbit at 51.60 degrees.

Stage Data - N-IM 1965

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 N1M 1965 - V. Gross Mass: 355,000 kg (782,000 lb). Empty Mass: 20,000 kg (44,000 lb). Thrust (vac): 2,940.000 kN (660,930 lbf). Isp: 347 sec. Burn time: 380 sec. Diameter: 4.80 m (15.70 ft). Span: 6.80 m (22.30 ft). Length: 20.00 m (65.00 ft). Propellants: Lox/Kerosene. No Engines: 4. Engine: 11D53M. Status: Study 1965. Comments: As per N1 improvement study, 1965. Further stretch of Block V.

Family: heavy-lift, orbital launch vehicle. Country: Russia. Engines: 11D51M, 11D52M, 11D53M. Stages: N1M 1965 - A, N1M 1965 - B, N1M 1965 - V. Agency: Korolev bureau.

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