RD-58S
Engine · Russia
Original archive entry. The text, images and links below are kept as they were written.
Credit: from Semenov, et. al., Buran, 1995.
Kosberg Lox/Kerosene rocket engine. Proton 8K82K / 11S861-01 stage 4 (block DM). Version 17D12 for Buran OMS. Version uses synthetic kerosene ('Sintin') for higher specific impulse. First flight 1994.
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.
Related
- Country
- Russia
- Launch Vehicles
- Proton-K/DM-2M, Proton-K/DM-2M DM3, Proton-K/DM-2M DM4
- Propellants
- Lox/Kerosene
- Stages
- Proton 11S861-01
- Agency
- Korolev bureau
Photo Gallery
Buran propulsion
Buran propulsion system diagram
Credit: from Semenov, et. al., Buran, 1995.
Buran ODU
Buran ODU engine system diagram
Credit: from Semenov, et. al., Buran, 1995.
Engine 11D68 detail
Close-up view of the 11D68 Block D lunar crasher stage showing detail of the BOZ orientation/ullage thrusters that control the stage during coast, restart, and manoeuvre.
Credit: © Mark Wade
