This page no longer updated from 31 October 2001. Latest version can be found at www.astronautix.com
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.
Back to Index
Last update 12 March 2001.
Definitions of Technical Terms.
Contact Mark Wade with any corrections or comments.
Conditions for use of drawings, pictures, or other materials from this site..
© Mark Wade, 2001 .