Engine Model: RD-119. Manufacturer Name: RD-119. Government Designation: 8D710. Designer: Glushko. Developed in: 1958-63. Application: Kosmos 1 stage 2. Propellants: Lox/UDMH. Thrust(vac): 105.500 kN (23,717 lbf). Thrust(sl): 65.600 kN (14,747 lbf). Isp: 352 sec. Isp (sea level): 220 sec. Burn time: 260 sec. Mass Engine: 168 kg (370 lb). Diameter: 1.02 m (3.34 ft). Length: 2.17 m (7.11 ft). Chambers: 1. Chamber Pressure: 78.94 bar. Area Ratio: 102.00. Oxidizer to Fuel Ratio: 1.50. Thrust to Weight Ratio: 63.75. Country: Russia. Status: Out of production. First Flight: 1961. Last Flight: 1977. Flown: 165. Glushko had built the RD-109, 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. Based on RD-109. However Glushko was able to have the engine adopted for the second stage of the Kosmos space launcher.
RD-119 used on Rocket Stages
Bibliography:- Kudryavtseva, V M, ed., Zhidkostnikh Raketnikh Dvigatley, Visshaya Shkola, Moscow, 1993.
- 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.
