This page no longer updated from 31 October 2001. Latest version can be found at RD-111

Manufacturer Name: RD-111. Government Designation: 8D716. Designer: Glushko. Developed in: 1959-62. Application: R-9 stage 1. Used on stages: R-9A Stage 1, YaKhR-2 Strap-on. Used on launch vehicles: R-9, YaKhR-2. Propellants: Lox/Kerosene Thrust(vac): 166,000 kgf. Thrust(vac): 1,628.00 kN. Isp: 317 sec. Isp (sea level): 275 sec. Burn time: 110 sec. Mass Engine: 1,492 kg. Diameter: 1.7 m. Length: 2.1 m. Chambers: 4. Chamber Pressure: 78.50 bar. Area Ratio: 18.00. Oxidizer to Fuel Ratio: 2.39. Thrust to Weight Ratio: 112.23. Country: Russia. Status: Out of Production. First Flight: 1962. References: 225 , 287 , 317 , 320 .

The 121-140,000 kgf RD-111 was developed for combat missiles. It had special flexible pipelines and gimbals (simpler than bellows). You’d expect pre-launch pressurisation to be simple and quick with a military missile but the LOX on the R-9 missile took two hours to load. It was just too complicated for military use and would have been knocked out by bombers let alone missiles before it could be used. The final version took just 20 minutes to prepare and veterans claimed just 10 minutes in their tests. It was used in both silo and pad based missiles. Diameter is per chamber.

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Last update 12 March 2001.
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© Mark Wade, 2001 .