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astronautix.com RD-160


Designer: Glushko. Developed in: 1993-. Application: Upper stage. Propellants: Lox/LCH4 Thrust(vac): 2,000 kgf. Thrust(vac): 19.60 kN. Isp: 381 sec. Burn time: 900 sec. Mass Engine: 129 kg. Diameter: 0.8 m. Length: 1.7 m. Chambers: 1. Chamber Pressure: 118.00 bar. Area Ratio: 352.00. Oxidizer to Fuel Ratio: 3.69. Country: Russia. Status: Developed 1993-. References: 325 . Comments: Methane version of upper stage engine RD-161 (1). Gimbaling +/- 6 degree in two planes. Status 1996 was RD-161 prototype, development estimated for four years. Nozzle expansion ratio is 120/0.05=2400. Prototype was RD-161.
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Last update 12 March 2001.
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