This page no longer updated from 31 October 2001. Latest version can be found at RD-100

Manufacturer Name: RD-100. Designer: Glushko. Developed in: 1946-50. Application: R-1, V-1A. Used on stages: R-1. Used on launch vehicles: R-1. Propellants: Lox/Alcohol Thrust(vac): 31,305 kgf. Thrust(vac): 304.00 kN. Isp: 237 sec. Isp (sea level): 203 sec. Burn time: 65 sec. Mass Engine: 885 kg. Diameter: 1.6 m. Length: 3.7 m. Chambers: 1. Chamber Pressure: 15.90 bar. Oxidizer to Fuel Ratio: 1.28. Thrust to Weight Ratio: 35.37. Country: Russia. Status: Out of Production. First Flight: 1953. References: 225 , 287 , 317 , 321 , 323 , 342 , 394 .

The RD-100 was a Russian copy of the V-2 engine using Russian materials - which made it very difficult! German rocket scientists assisted in its realization. German salaries and conditions were good - the chief of the German team receiving the second highest salary after the Soviet designer-in-chief. The RD-100 was built in 1946 at a former Ilyushin aviation plant that had been moved to Tashkent in World War 2 (now the Energomash factory). There was no equipment so everything had to be started from scratch. By mid-1947 the first RD-100 was ready. In May 1948 the first RD-100 test took place at Khimki itself, with the spectators watching from 1 km away. There are still tests at the same location but thrust levels are now 800 tonnes force. The R-1 rocket with the RD-100 engine entered service in 1950.

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 .