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RD-264
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Manufacturer Name: RD-264. Government Designation: 11D119. Designer: Glushko. Developed in: 1969-73. Application: R-36M / RS-20A (SS-18 Mod 1) stage 1. Propellants: N2O4/UDMH. Thrust(vac): 4,521.000 kN (1,016,361 lbf). Isp: 318 sec. Isp (sea level): 293 sec. Mass Engine: 3,600 kg (7,900 lb). Diameter: 3.03 m (9.92 ft). Length: 2.15 m (7.05 ft). Chambers: 4. Chamber Pressure: 206.00 bar. Oxidizer to Fuel Ratio: 2.67. Thrust to Weight Ratio: 128.05. Country: Russia. First Flight: 1986. Last Flight: 2006. Flown: 42. Consists of four RD-263 engines.
RD-264 used on Rocket Stages
Bibliography and Further Reading - Rakhmanin, V F, Odnazhdy i Navsegda, NPO Energomash, Moscow 1998 via Dietrich Haeseler. Biography and history of development of the rocket motors of Glushko.
- Haeseler, Dietrich, Information from NPO Energia museum exhibit, Nov. 1992 via Dietrich Haeseler.
- Russian Arms Catalogue, Vol 5 and 6, Military Parade, Moscow via Dietrich Haeseler.
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© Mark Wade, 1997 - 2007 except where otherwise noted.
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