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|N1-L3 - 1964 - N1-L3 as per advanced project, 1964|
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Family: N. Country: Russia. Status: Study 1965.
The N-IU would be the initial production version of the N1 following the mad rush to make the lunar landings. It would have essentially the same payload but would be substantially re-engineered for sharply improved reliability, most notably with autonomously operating engines. It is interesting to note that four years before the disastorous first flight Korolev already foresaw the potential engine problems that would be the downfall of the project.
LEO Payload: 95,000 kg. to: 220 km Orbit. at: 51.6 degrees. Liftoff Thrust: 4,500,000 kgf. Total Mass: 2,750,000 kg. Core Diameter: 17.0 m. Total Length: 105.0 m.
- Stage Number: 1. 1 x N1U 1965 - A Gross Mass: 1,934,000 kg. Empty Mass: 195,000 kg. Thrust (vac): 5,040,000 kgf. Isp: 331 sec. Burn time: 110 sec. Isp(sl): 296 sec. Diameter: 10.0 m. Span: 17.0 m. Length: 30.0 m. Propellants: Lox/Kerosene No Engines: 30. NK-15
- Stage Number: 2. 1 x N1U 1965 - B Gross Mass: 506,000 kg. Empty Mass: 50,000 kg. Thrust (vac): 1,400,000 kgf. Isp: 346 sec. Burn time: 110 sec. Diameter: 6.8 m. Span: 9.8 m. Length: 20.0 m. Propellants: Lox/Kerosene No Engines: 8. NK-15V
- Stage Number: 3. 1 x N1U 1965 - V Gross Mass: 193,000 kg. Empty Mass: 15,000 kg. Thrust (vac): 160,000 kgf. Isp: 347 sec. Burn time: 380 sec. Diameter: 4.8 m. Span: 6.8 m. Length: 12.0 m. Propellants: Lox/Kerosene No Engines: 4. NK-19
- 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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