Engine Model: RD-185. Manufacturer Name: RD-185. Designer: Glushko. Developed in: 1996-. Application: Riksha-0 stage 2. Propellants: Lox/LCH4. Thrust(vac): 179.000 kN (40,240 lbf). Isp: 378 sec. Mass Engine: 415 kg (914 lb). Diameter: 1.50 m (4.90 ft). Length: 3.30 m (10.80 ft). Chambers: 1. Chamber Pressure: 147.00 bar. Oxidizer to Fuel Ratio: 3.40. Thrust to Weight Ratio: 43.97. Country: Russia. Status: Developed 1996-. Upper stage version of RD-169 with larger nozzle. Gimbaling +/- 4 degree in two planes. Status 1996 was project, development estimated for four years. Nozzle expansion ratio is 150/0.036=4167.
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.