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Engine Model: RD-120. Manufacturer Name: RD-120. Government Designation: 11D123. Designer: Glushko. Developed in: 1976-85. Application: Zenit stage 2. Propellants: Lox/Kerosene. Thrust(vac): 833.000 kN (187,265 lbf). Isp: 350 sec. Burn time: 315 sec. Mass Engine: 1,125 kg (2,480 lb). Diameter: 1.95 m (6.38 ft). Length: 3.87 m (12.70 ft). Chambers: 1. Chamber Pressure: 162.80 bar. Area Ratio: 106.70. Oxidizer to Fuel Ratio: 2.60. Thrust to Weight Ratio: 75.55. Country: Russia. Status: In production. First Flight: 1985. Last Flight: 2006. Flown: 60.

The RD-120 is a high altitude engine used in the Zenit second stage. It was the first batch produced Russian engine to be test fired in the United States (3 test burns were made). Mass is wet mass.

Engine Model: RD-120.01. Manufacturer Name: RD-120.01. Designer: Glushko. Propellants: Lox/Kerosene. Thrust(vac): 784.000 kN (176,250 lbf). Isp: 329 sec. Chambers: 1. Country: Russia. Status: Design concept.

Engine Model: RD-120.03. Manufacturer Name: RD-120.03. Designer: Glushko. Propellants: Lox/Kerosene. Thrust(vac): 882.000 kN (198,281 lbf). Isp: 353 sec. Chambers: 1. Country: Russia. Status: Design concept.

Engine Model: RD-120K. Manufacturer Name: RD-120K. Other Designations: RD-123. Designer: Glushko. Application: Soyuz M stage 1, 2. Proposed for X-34. Propellants: Lox/Kerosene. Thrust(vac): 873.000 kN (196,258 lbf). Thrust(sl): 866.900 kN (194,887 lbf). Throttled thrust(vac): 794.000 kN (178,498 lbf). Isp: 336 sec. Isp (sea level): 298 sec. Burn time: 305 sec. Mass Engine: 1,433 kg (3,159 lb). Diameter: 1.50 m (4.90 ft). Length: 2.80 m (9.10 ft). Chambers: 1. Chamber Pressure: 172.00 bar. Oxidizer to Fuel Ratio: 2.60. Thrust to Weight Ratio: 62.10. Country: Russia. Status: Design 1994.

Sea-level variant of RD-120. Thrust and Isp range due to throat diam. and chamber pressure. Gimbaling +/- 6 degree in two planes. Status 1996 was RD-120 prototype with 1.8 m diam., development estimated for three years. Chamber pressure 163 - 172 bar.

Engine Model: RD-120M. Manufacturer Name: RD-120M. Designer: Glushko. Developed in: 1995. Application: PacAstro-2 stage 1. Propellants: Lox/Kerosene. Thrust(vac): 850.400 kN (191,178 lbf). Isp: 331 sec. Isp (sea level): 304 sec. Mass Engine: 1,080 kg (2,380 lb). Diameter: 1.40 m (4.50 ft). Length: 2.44 m (7.99 ft). Chambers: 1. Chamber Pressure: 176.30 bar. Area Ratio: 4.96. Oxidizer to Fuel Ratio: 2.60. Thrust to Weight Ratio: 80.29. Country: Russia. Status: Out of Production.

Sea-level variant of RD-120 engine, similar to RD-120K. Gimbaling +/- 6 degree in two planes.

RD-120 used on Rocket Stages
Bibliography:

  • Salmon, Andrew, The Story Of Russian Rocket Engines - Energomash Museum, Commentary by the guide at the Energomash rocket engine museum in Khimki, April 1998 at YSC98..
  • Klepikov, Katorgin, Chvanov, IAF-Congress Turin, 1997, "The New Generation of Rocket Engines, Operating by Ecologically Safe Propellant ...", IAF-97-S.1.03 via Dietrich Haeseler.
  • Sutton, G P, Rocket Propulsion Elements, John Wiley and Sons, 1991 via Dietrich Haeseler.
  • Novosti kosmonavtiki, Issue 15, 1995.
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