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Buran RCS
Credit - from Semenov, et. al., Buran, 1995.
Engine Model: 17D11. Government Designation: 17D11. Designer: Korolev. Developed in: 1976-88. Application: Buran OMS and verniers. Propellants: Lox/Kerosene. Thrust(vac): 86.300 kN (19,401 lbf). Isp: 362 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. Status: Out of Production.

Buran orbital propulsion system, including 2 x 17D12, 38 x 17D15, 8 x RDMT-200K

Engine Model: 17D12. Government Designation: 17D12. Designer: Korolev. Developed in: 1976-88. Application: Buran OMS. Propellants: Lox/Kerosene. Thrust(vac): 86.300 kN (19,401 lbf). Isp: 362 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. Status: Out of Production.

Version of RD-58 for Buran orbital propulsion system 17D11. Uses synthetic kerosene ('Sintin') for higher specific impulse. Some data differ for 17D12 in Energia 92 compared to RD-58S (Energia 92): Area Ratio 192, Ivac 362 s, pc 78.5 bar. 15 ignitions.

Engine Model: RD-58. Manufacturer Name: RD-58. Government Designation: 11D58. Designer: Korolev. Developed in: 1964-68. Application: N-1 stage 5; Proton 8K82K / 11S824 stage 4 (block D). Propellants: Lox/Kerosene. Thrust(vac): 83.400 kN (18,749 lbf). Isp: 349 sec. Burn time: 600 sec. Mass Engine: 300 kg (660 lb). Diameter: 1.17 m (3.83 ft). Chambers: 1. Chamber Pressure: 78.00 bar. Area Ratio: 189.00. Thrust to Weight Ratio: 28.33. Country: Russia. First Flight: 1967. Last Flight: 1988. Flown: 45.

High-performance upper-stage engine developed for N1 lunar crasher stage, but adopted before that could fly as upper stage of Proton launch vehicle. Kerosene changed from T-1 to RG-1 to achieve sufficient chamber cooling.

Engine Model: RD-58M. Manufacturer Name: RD-58M. Government Designation: 11D58M. Designer: Korolev. Developed in: 1970-74. Application: Proton 8K824K / 11S824M; 11S824F; 11S86; 11S861; 17S40 stage 4 (block DM). Propellants: Lox/Kerosene. Thrust(vac): 83.400 kN (18,749 lbf). Isp: 353 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: 77.50 bar. Area Ratio: 189.00. Oxidizer to Fuel Ratio: 2.48. Thrust to Weight Ratio: 36.95. Country: Russia. Status: In production. First Flight: 1974. Last Flight: 2006. Flown: 212.

Engine Model: RD-58MF. Manufacturer Name: RD-58MF. Government Designation: 11D58MF. Designer: Korolev. Application: Zenit stage 3 (block DM-SL), upper stage projects N12RA, Proryv, LM, 315GK for Zenit, Angara, Energia-M. Propellants: Lox/Kerosene. Thrust(vac): 83.400 kN (18,749 lbf). Isp: 353 sec. Burn time: 660 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: 77.50 bar. Area Ratio: 189.00. Thrust to Weight Ratio: 36.95. Country: Russia. Status: In Production.

Multi-function variant of RD-58 for uprated upper stages for future applications. Block-DM-SL for Sea-Launch may have used RD-58M.

Engine Model: RD-58S. 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.

Engine Model: RD-58Z. Manufacturer Name: RD-58Z. Government Designation: 11D58Z. Designer: Korolev. Application: Zenit stage 3. Propellants: Lox/Kerosene. Thrust(vac): 71.000 kN (15,961 lbf). Isp: 361 sec. Burn time: 660 sec. Mass Engine: 300 kg (660 lb). Diameter: 2.90 m (9.50 ft). Chambers: 1. Chamber Pressure: 78.00 bar. Area Ratio: 189.00. Thrust to Weight Ratio: 24.13. Country: Russia. Status: Developed 1981-1990.

RD-58 used on Rocket Stages
  • Used on stage: Block D. on launch vehicle: N1.
RD-58 used on Spacecraft
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