Credit: © Mark Wade
Glushko lox/udmh rocket engine. 105.5 kN. Kosmos 1 stage 2. Out of production. Isp=352s. Derived from RD-109 motor originally intended for the second stage of a Lox/UDMH version of the R-7. First flight 1961.
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.
Application: Kosmos 1 stage 2.
Thrust (sl): 65.600 kN (14,747 lbf). Thrust (sl): 6,694 kgf. Engine: 168 kg (370 lb). Chamber Pressure: 78.94 bar. Area Ratio: 102. Thrust to Weight Ratio: 63.75. Oxidizer to Fuel Ratio: 1.5.
More... - Chronology...
Status: Out of production.
Unfuelled mass: 168 kg (370 lb).
Height: 2.17 m (7.11 ft).
Diameter: 1.02 m (3.34 ft).
Thrust: 105.50 kN (23,717 lbf).
Specific impulse: 352 s.
Specific impulse sea level: 220 s.
Burn time: 260 s.
First Launch: 1958-63.
Number: 165 .
Associated Launch Vehicles
Kosmos 63S1 Ukrainian orbital launch vehicle. The 63S1 initial production version was used through May 1966 for a total of 40 launches, of which 12 were failures. It was succeeded by the 63S1M prototype for the 11K63 production space launcher. More...
Kosmos 11K63 Ukrainian orbital launch vehicle. Series production version of satellite launcher based on Yangel R-12 IRBM. Succeeded 63S1M prototype from 1965, using same 'Dvina' launch complex. From March 16, 1967 orbital launches from Plesetsk were from the purpose-built 'Raduga' launch complex LC133. Total of 123 launches, of which 8 were failures. More...
Kosmos 63S1M Ukrainian orbital launch vehicle. Modernized version of 63S1 initial configuration of the first Kosmos launcher and the prototype for the production 11K63 launch vehicle. Suborbital launches from Plesetsk from 1965 at from the modified R-12 silo 'Dvina'. Flown only a few times in 1965-1967. Succeeded by the 11K63 production model launched from the 'Raduga' complex. More...
Associated Manufacturers and Agencies
Glushko Russian manufacturer of rocket engines and rockets. Glushko Design Bureau, Russia. More...
Lox/UDMH Liquid oxygen was the earliest, cheapest, safest, and eventually the preferred oxidiser for large space launchers. Its main drawback is that it is moderately cryogenic, and therefore not suitable for military uses where storage of the fuelled missile and quick launch are required. Unsymmetrical Dimethylhydrazine ((CH3)2NNH2) became the storable liquid fuel of choice by the mid-1950's. Development of UDMH in the Soviet Union began in 1949. It is used in virtually all storable liquid rocket engines except for some orbital manoeuvring engines in the United States, where MMH has been preferred due to a slightly higher density and performance. More...
Varfolomyev, Timothy, "Soviet Rocketry that Conquered Space - Part 2", Spaceflight, 1996, Volume 38, page 48.
Kudryavtseva, V M, ed., Zhidkostnikh Raketnikh Dvigatley, Visshaya Shkola, Moscow, 1993.
Glushko, V P, Albom Konstruktsiy ZhRD, Vol. 1 1968, Vol. 3 & 4 1969 via Dietrich Haeseler.
S1 Lox/UDMH propellant rocket stage. Loaded/empty mass 8,595/840 kg. Thrust 105.51 kN. Vacuum specific impulse 352 seconds. More...
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