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astronautix.com N-IM 1965

N-IM 1965
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.


Specifications

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.



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Last update 12 March 2001.
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