Engine Model: RD-183. Manufacturer Name: RD-183. Designer: Glushko. Developed in: 1996-. Application: Riksha (-0, -1, -2) apogee stage. Propellants: Lox/LCH4. Thrust(vac): 9.800 kN (2,203 lbf). Isp: 360 sec. Mass Engine: 60 kg (132 lb). Diameter: 0.31 m (1.01 ft). Length: 1.15 m (3.77 ft). Chambers: 1. Chamber Pressure: 73.50 bar. Oxidizer to Fuel Ratio: 3.40. Thrust to Weight Ratio: 16.65. Country: Russia. Status: Developed 1996-. Main engine for apogee stage of Riksha-1 launcher project. Gimbaling +/- 10 degree in two planes. Status 1996 was project, development estimated for four years. Nozzle expansion ratio is 75/0.055=1364.
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.