RD-58M

Block D / 11D68
Credit - © Mark Wade

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.

RD-58M used on Rocket Stages

Used on stage: Proton 11S824F. on launch vehicle: Proton 8K82K / 11S824F.

Used on stage: Proton 11S824M. on launch vehicle: Proton 8K82K / 11S824M.

Used on stage: Proton 11S86. on launch vehicle: Proton 8K82K / 11S86.

Used on stage: Proton 11S861. on launch vehicle: Proton 8K82K / 11S861.

Used on stage: Proton 17S40. on launch vehicle: Proton 8K82K / 17S40.

Used on stage: Zenit-3. on launch vehicle: Kvant.

Used on stage: Zenit-3. on launch vehicle: Zenit-3SL.

RD-58M used on Spacecraft

Used on: Block D-1 11S824M.

Used on: Block D-2 11S824F.

Used on: Block DM 11S86.

Used on: Block DM-2 11S861.

Used on: Block DM-5 17S40.

Bibliography and Further Reading

Haeseler, Dietrich, Information from NPO Energia museum exhibit, Nov. 1992 via Dietrich Haeseler.

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 Superseded by the later editions.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...

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© Mark Wade, 1997 - 2007 except where otherwise noted.

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