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.

RD-120K used on Rocket Stages

Used on stage: Kvant. on launch vehicle: Kvant.

Used on stage: Kvant-1. on launch vehicle: Kvant-1.

Used on stage: Soyuz M-0. on launch vehicle: Soyuz M.

Used on stage: Soyuz M-1. on launch vehicle: Soyuz M.

Bibliography and Further Reading

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.

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