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astronautix.com 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.

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Last update 12 March 2001.
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