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| N1 24 engine version - N1 24 Engine Design of 1962 Credit: © Mark Wade. 2,017 bytes. 97 x 372 pixels. |
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Family: N. Country: Russia. Status: Study 1962.
Final configuration of N1 at time of development go-ahead. 75 tonne payload selected to support OS-1 heavy space station program.
SpecificationsLiftoff Thrust: 3,459,640 kgf. Total Mass: 2,110,000 kg. Core Diameter: 10.0 m. Total Length: 74.0 m.
- Stage Number: 1. 1 x N1 1962 - A Gross Mass: 1,384,000 kg. Empty Mass: 117,000 kg. Thrust (vac): 4,020,000 kgf. Isp: 331 sec. Burn time: 103 sec. Isp(sl): 296 sec. Diameter: 10.0 m. Span: 17.0 m. Length: 30.0 m. Propellants: Lox/Kerosene No Engines: 24. NK-15
- Stage Number: 2. 1 x N1 1962 - B Gross Mass: 506,000 kg. Empty Mass: 50,000 kg. Thrust (vac): 1,405,000 kgf. Isp: 347 sec. Burn time: 106 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 N1 1962 - V Gross Mass: 193,000 kg. Empty Mass: 16,000 kg. Thrust (vac): 160,000 kgf. Isp: 347 sec. Burn time: 368 sec. Diameter: 4.8 m. Span: 6.8 m. Length: 12.0 m. Propellants: Lox/Kerosene No Engines: 4. NK-19
Bibliography:- 89 - Semenov, Yu. P., S P Korolev Space Corporation Energia, RKK Energia, 1994.
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Last update 12 March 2001.
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© Mark Wade, 2001 .