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RD-109

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RD-109 Credit: © Mark Wade

AKA: 8D711;GDU-10. Status: Developed 1957-60. Date: 1957-60. Thrust: 101.60 kN (22,841 lbf). Unfuelled mass: 210 kg (460 lb). Specific impulse: 334 s. Burn time: 330 s. Height: 2.28 m (7.48 ft). Diameter: 1.02 m (3.36 ft).

Intended for the second stage of a Lox/UDMH version of the R-7. Glushko expected to improve engine specific impulse by 8 to 10 seconds over that of the Lox/Kerosene R-7 engines. The project was abandoned because of Korolev's refusal to use such a toxic fuel. However the engine became the basis of the RD-119 used on the Kosmos space launcher.

Engine: 210 kg (460 lb). Chamber Pressure: 77.50 bar. Area Ratio: 58.5. Thrust to Weight Ratio: 49.33. Oxidizer to Fuel Ratio: 1.49.

RD-119 Glushko LOx/UDMH rocket engine. Kosmos 1 stage 2. Out of production. Derived from RD-109 motor originally intended for the second stage of a LOx/UDMH version of the R-7. First flight 1961.