Engine Model: RD-109. Manufacturer Name: RD-109. Government Designation: 8D711. Other Designations: GDU-10. Designer: Glushko. Developed in: 1957-60. Application: 8K73 stage 2. Propellants: Lox/UDMH. Thrust(vac): 101.600 kN (22,841 lbf). Isp: 334 sec. Burn time: 330 sec. Mass Engine: 210 kg (460 lb). Diameter: 1.02 m (3.36 ft). Length: 2.28 m (7.48 ft). Chambers: 1. Chamber Pressure: 77.50 bar. Area Ratio: 58.50. Oxidizer to Fuel Ratio: 1.49. Thrust to Weight Ratio: 49.33. Country: Russia. Status: Developed 1957-60. First Flight: 1960. 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.
Bibliography:- NASA Shuttle and ISS Mission Press Kits and News Releases, NASA, 1981-present. Web Address when accessed: http://www.nasa.gov/.
- NASA Shuttle-Mir Web, NASA, 1997. Web Address when accessed: http://shuttle-mir.nasa.gov/ops/mir/.
- Varfolomyev, Timothy, Spaceflight, "Soviet Rocketry that Conquered Space - Part 2", 1996, Volume 38, page 48.
- Glushko, V P, Albom Konstruktsiy ZhRD, Vol. 1 1968, Vol. 3 & 4 1969 via Dietrich Haeseler.
