Glushko N2O4/Aerozine-50 rocket engine. 117.6 kN. Experimental engine. Study 1961. Experimental engine using Aerozine 50 (50% UDMH + 50% hydrazine) as fuel. Isp=350s.
Application: Experimental engine.
Engine: 174 kg (383 lb). Chamber Pressure: 147.00 bar. Thrust to Weight Ratio: 68.91. Oxidizer to Fuel Ratio: 1.718.
Status: Study 1961.
More... - Chronology...
Unfuelled mass: 174 kg (383 lb).
Height: 2.20 m (7.20 ft).
Diameter: 1.27 m (4.15 ft).
Thrust: 117.60 kN (26,438 lbf).
Specific impulse: 350 s.
First Launch: 1963-65.
Associated Manufacturers and Agencies
Glushko Russian manufacturer of rocket engines and rockets. Glushko Design Bureau, Russia. More...
N2O4/Aerozine-50 Nitrogen tetroxide became the storable liquid propellant of choice from the late 1950's. Aerozine was a 50-50 mixture of hydrazine and UDMH developed for use in the Titan 2 missile. Copied in one Russian missile but otherwise straight UDMH used more commonly. Higher boiling point than UDMH. More...
Haeseler, Dietrich, Information from NPO Energomash museum exhibit, Nov. 1992 via Dietrich Haeseler.
R-56 Block K N2O4/Aerozine-50 propellant rocket stage. Loaded/empty mass 9,400/700 kg. Thrust 117.00 kN. Vacuum specific impulse 350 seconds. Empty mass estimated (rounded figures given in source material indicates impossible 9 tonnes gross with 8.7 tonnes propellant). More...
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