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NK-31
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Manufacturer Name: NK-31. Government Designation: 11D114. Designer: Kuznetsov. Developed in: 1969-74. Application: N-1F stage 4 (block G). Propellants: Lox/Kerosene. Thrust(vac): 402.000 kN (90,373 lbf). Isp: 353 sec. Burn time: 1,200 sec. Mass Engine: 722 kg (1,591 lb). Diameter: 1.40 m (4.50 ft). Chambers: 1. Chamber Pressure: 92.00 bar. Area Ratio: 124.00. Oxidizer to Fuel Ratio: 2.60. Thrust to Weight Ratio: 56.78. Country: Russia. Status: Study 1993. First Flight: 1974. To have been used in the N-1F fourth (Block G translunar injection) stage. After initial failures of the N-1 Kuznetsov developed modified versions of engines for all four stages, which had multiple ignition capability and increased operational lifetime.
NK-31 used on Rocket Stages
Bibliography and Further Reading - Data sheets NPO Trud via Dietrich Haeseler.
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© Mark Wade, 1997 - 2007 except where otherwise noted.
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