This page no longer updated from 31 October 2001. Latest version can be found at RD-183

Manufacturer Name: RD-183. Designer: Glushko. Developed in: 1996-. Application: Riksha (-0, -1, -2) apogee stage. Propellants: Lox/LCH4 Thrust(vac): 999 kgf. Thrust(vac): 9.80 kN. Isp: 360 sec. Mass Engine: 60 kg. Diameter: 0.3 m. Length: 1.1 m. Chambers: 1. Chamber Pressure: 73.50 bar. Oxidizer to Fuel Ratio: 3.40. Country: Russia. Status: Developed 1996-. References: 325 . Comments: 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.
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 .