This page no longer updated from 31 October 2001. Latest version can be found at 17D11

Buran RCS
Buran RCS - Buran orientation engine

Credit: from Semenov, et. al., Buran, 1995.. 27,637 bytes. 259 x 409 pixels.

Government Designation: 17D11. Designer: Korolev. Developed in: 1976-88. Application: Buran OMS and verniers. Used on spacecraft: Buran. Propellants: Lox/Kerosene Thrust(vac): 8,800 kgf. Thrust(vac): 86.30 kN. Isp: 362 sec. Burn time: 680 sec. Mass Engine: 230 kg. Diameter: 1.2 m. Length: 2.3 m. Chambers: 1. Chamber Pressure: 79.40 bar. Area Ratio: 189.00. Oxidizer to Fuel Ratio: 2.42. Country: Russia. Status: Out of Production. References: 95 , 315 . Comments: Buran orbital propulsion system, including 2 x 17D12, 38 x 17D15, 8 x RDMT-200K.
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Last update 12 March 2001.
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