This page no longer updated from 31 October 2001. Latest version can be found at RD-264

Manufacturer Name: RD-264. Government Designation: 11D119. Designer: Glushko. Developed in: 1969-73. Application: R-36M / RS-20A (SS-18 Mod 1) stage 1. Used on stages: R-36M2-1. Used on launch vehicles: Dnepr. Propellants: N2O4/UDMH Thrust(vac): 461,000 kgf. Thrust(vac): 4,521.00 kN. Isp: 318 sec. Isp (sea level): 293 sec. Mass Engine: 3,600 kg. Diameter: 3.0 m. Length: 2.1 m. Chambers: 4. Chamber Pressure: 206.00 bar. Oxidizer to Fuel Ratio: 2.67. Country: Russia. Status: Out of Production. First Flight: 1990. References: 315 , 323 , 342 . Comments: Consists of four RD-263 engines.
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Last update 12 March 2001.
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© Mark Wade, 2001 .