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|N-IM 1965 - N-IM version of 1965|
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Family: N. Country: Russia. Status: Study 1965.
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 tonnes 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 tonnes each and the second and third stages again enlarged.
LEO Payload: 155,000 kg. to: 220 km Orbit. at: 51.6 degrees. Liftoff Thrust: 7,500,000 kgf. Total Mass: 4,950,000 kg. Core Diameter: 17.0 m. Total Length: 135.0 m.
- Stage Number: 1. 1 x N1M 1965 - A Gross Mass: 3,800,000 kg. Empty Mass: 375,000 kg. Thrust (vac): 8,700,000 kgf. Isp: 330 sec. Burn time: 130 sec. Isp(sl): 296 sec. Diameter: 10.0 m. Span: 17.0 m. Length: 50.0 m. Propellants: Lox/Kerosene No Engines: 30. 11D51M
- Stage Number: 2. 1 x N1M 1965 - B Gross Mass: 620,000 kg. Empty Mass: 75,000 kg. Thrust (vac): 2,240,000 kgf. Isp: 346 sec. Burn time: 85 sec. Diameter: 6.8 m. Span: 9.8 m. Length: 30.0 m. Propellants: Lox/Kerosene No Engines: 8. 11D52M
- Stage Number: 3. 1 x N1M 1965 - V Gross Mass: 355,000 kg. Empty Mass: 20,000 kg. Thrust (vac): 300,000 kgf. Isp: 347 sec. Burn time: 380 sec. Diameter: 4.8 m. Span: 6.8 m. Length: 20.0 m. Propellants: Lox/Kerosene No Engines: 4. 11D53M
- 283 - Vetrov, G S, S. P. Korolev i evo delo, Nauka, Moscow, 1998.
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Last update 12 March 2001.
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