This page no longer updated from 31 October 2001. Latest version can be found at RD-103

Manufacturer Name: RD-103. Government Designation: 8D52. Other Designations: 8D71. Designer: Glushko. Developed in: 1947-53. Application: R-5. Propellants: Lox/Alcohol Thrust(vac): 51,000 kgf. Thrust(vac): 500.00 kN. Isp: 243 sec. Isp (sea level): 216 sec. Burn time: 120 sec. Mass Engine: 870 kg. Diameter: 1.6 m. Length: 3.1 m. Chambers: 1. Chamber Pressure: 23.90 bar. Country: Russia. Status: Out of Production. First Flight: 1953. References: 225 , 319 , 323 , 394 .

Final extrapolation of the V-2 rocket engine in Russia. Designer at OKB-456 was V A Vitkin. Glushko states 'thus ended the German page' of German engine technology in the USSR (this ignores the fact that the German ED-140 design provided the basis for the entire next generation of Soviet rocket engines). The engine introduced automatic thrust regulation in flight, a feature first advocated by Groettrup's German team for the G-1 engine.

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 .