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N-IM 1965
Part of N1
N-IM 1965
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



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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