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17D11
Part of RD-58 Family
Buran RCS
Buran RCS
Buran orientation engine
Credit: from Semenov, et. al., Buran, 1995.
Kosberg Lox/Kerosene rocket engine. Buran OMS and verniers. Out of Production. Buran orbital propulsion system, including 2 x 17D12, 38 x 17D15, 8 x RDMT-200K

Status: Out of Production. Date: 1976-88. Thrust: 86.30 kN (19,401 lbf). Unfuelled mass: 230 kg (500 lb). Specific impulse: 362 s. Burn time: 680 s. Height: 2.27 m (7.44 ft). Diameter: 1.17 m (3.83 ft).

Engine: 230 kg (500 lb). Chamber Pressure: 79.40 bar. Area Ratio: 189. Thrust to Weight Ratio: 38.26. Oxidizer to Fuel Ratio: 2.42.



Country: Russia. Propellants: Lox/Kerosene. Agency: Korolev bureau. Bibliography: 21, 315, 404, 42, 95.

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