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Buran main engine
Buran main engine -

Credit: from Semenov, et. al., Buran, 1995.. 21,365 bytes. 216 x 356 pixels.

Manufacturer Name: RD-58S. Government Designation: 11D58S. Designer: Korolev. Developed in: 1982-86. Application: Proton 8K82K / 11S861-01 stage 4 (block DM). Version 17D12 for Buran OMS. Used on stages: Proton 11S861-01. Used on launch vehicles: Proton 8K82K / 11S861-01, Proton 8K82K / DM3, Proton 8K82K / DM4. Propellants: Lox/Kerosene Thrust(vac): 8,800 kgf. Thrust(vac): 86.30 kN. Isp: 361 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: In Production. First Flight: 1994. Last Flight: 1999. Flown: 14. References: 42 , 315 . Comments: Version uses synthetic kerosene ('Sintin') for higher specific impulse.

Buran propulsionBuran propulsion - Buran propulsion system diagram

Credit: from Semenov, et. al., Buran, 1995.. 39,403 bytes. 316 x 447 pixels.

Buran ODUBuran ODU - Buran ODU engine system diagram

Credit: from Semenov, et. al., Buran, 1995.. 16,624 bytes. 222 x 297 pixels.

Engine 11D68 detailEngine 11D68 detail - Closeup view of the 11D68 Block D lunar crasher stage showing detiail of the BOZ orientation/ullage thrusters that control the stage during coast, restart, and maneuver.

Credit: © Mark Wade. 43,376 bytes. 393 x 424 pixels.

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Last update 12 March 2001.
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