This page no longer updated from 31 October 2001. Latest version can be found at www.astronautix.com
Manufacturer Name: RD-0202. Government Designation: 8D45. Designer: Kosberg. Developed in: 1961-64. Application: UR-200 stage 1. Used on stages: UR-200 Stage 1. Used on launch vehicles: Initial UR-500, UR-200. Propellants: N2O4/UDMH Thrust(vac): 228,000 kgf. Thrust(vac): 2,236.00 kN. Isp: 311 sec. Isp (sea level): 278 sec. Burn time: 136 sec. Mass Engine: 1,525 kg. Length: 1.8 m. Chambers: 4. Area Ratio: 29.80. Oxidizer to Fuel Ratio: 2.60. Country: Russia. Status: Developed 1961-64. First Flight: 1964. References: 309 . Comments: Engine unit (DU - dvigatelnaya ustanovka) consisting of 1 RD-0204 for tank pressurization and three RD-0203.
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 .