RD-182 home
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Engine Model: RD-182. Manufacturer Name: RD-182. Other Designations: RD-120M. Designer: Glushko. Developed in: 1994-. Application: Riksha (-1, -2) stage 1. Propellants: Lox/LOX/LCH4. Thrust(vac): 902.000 kN (202,777 lbf). Throttled thrust(vac): 814.000 kN (182,994 lbf). Isp: 353 sec. Isp (sea level): 316 sec. Mass Engine: 1,500 kg (3,300 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: 3.40. Thrust to Weight Ratio: 61.33. Country: Russia. Status: Developed 1994-.

Methane variant of RD-120K engine. Thrust range and Isp range due to throat diam. and chamber pressure. Gimbaling +/- 6 degree in two planes. Status 1996 was RD-120K, development estimated for three years. Chamber pressure 163 - 172.

Engine Model: RD-182M. Manufacturer Name: RD-182M. Designer: Glushko. Developed in: 1998-. Application: Vozdushnyy Start stage 1. Propellants: Lox/LNG. Thrust(vac): 882.000 kN (198,281 lbf). Chambers: 1. Country: Russia. Status: Developed 1998-.

Variant of RD-182 engine for liquid natural gas (mainly CH4). Proposed initial candidate for project Vozdushnyy Start of Kompomash.

Bibliography:

  • 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.
  • Polovnikov S P; Karpov, A S, Vestnik Aviatsii i Kosmonavtiki, "Projekt 'Vozdushnyy Start'", Moscow, 1-2/98 via Dietrich Haeseler.
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