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RD-58S
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 | Buran main engine
Credit - from Semenov, et. al., Buran, 1995.
Media Gallery
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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. Propellants: Lox/Kerosene. Thrust(vac): 86.300 kN (19,401 lbf). Isp: 361 sec. Burn time: 680 sec. Mass Engine: 230 kg (500 lb). Diameter: 1.17 m (3.83 ft). Length: 2.27 m (7.44 ft). Chambers: 1. Chamber Pressure: 79.40 bar. Area Ratio: 189.00. Oxidizer to Fuel Ratio: 2.42. Thrust to Weight Ratio: 38.26. Country: Russia. First Flight: 1994. Last Flight: 2006. Flown: 43. Version uses synthetic kerosene ('Sintin') for higher specific impulse.
RD-58S used on Rocket Stages
RD-58S used on Spacecraft
Bibliography and Further Reading - Isakowitz, Steven J,, International Reference to Space Launch Systems Second Edition, AIAA, Washington DC, 1991 (succeeded by 2000 edition). ISBN: 1563473534. Superseded by the later editions. More at amazon.com...
- Haeseler, Dietrich, Information from NPO Energia museum exhibit, Nov. 1992 via Dietrich Haeseler.
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