Engine Model: RD-160. Designer: Glushko. Developed in: 1993-. Application: Upper stage. Propellants: Lox/LCH4. Thrust(vac): 19.600 kN (4,406 lbf). Isp: 381 sec. Burn time: 900 sec. Mass Engine: 129 kg (284 lb). Diameter: 0.76 m (2.51 ft). Length: 1.70 m (5.50 ft). Chambers: 1. Chamber Pressure: 118.00 bar. Area Ratio: 352.00. Oxidizer to Fuel Ratio: 3.69. Thrust to Weight Ratio: 15.50. Country: Russia. Status: Developed 1993-. Methane version of lox/kerosene upper stage engine RD-161 (1). Gimbaling +/- 6 degree in two planes. Status 1996 was that RD-161 prototype had been completed, development of a methane version was estimated to take four years. Nozzle expansion ratio is 120/0.05=2400.
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.