Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z
RD-58S
Part of RD-58 Family
Buran main engine
Buran main engine
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.

AKA: 11D58S. Date: 1982-86. Number: 43 . Thrust: 86.30 kN (19,401 lbf). Unfuelled mass: 230 kg (500 lb). Specific impulse: 361 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. 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 propulsionBuran propulsion
Buran propulsion system diagram
Credit: from Semenov, et. al., Buran, 1995.


Buran ODUBuran ODU
Buran ODU engine system diagram
Credit: from Semenov, et. al., Buran, 1995.


Engine 11D68 detailEngine 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



Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z
© 1997-2017 Mark Wade - Contact
© / Conditions for Use