Encyclopedia Astronautica

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.
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.

More... - Chronology...

Associated Countries
See also
Associated Manufacturers and Agencies
  • Glushko Russian manufacturer of rocket engines and rockets. Glushko Design Bureau, Russia. More...

Associated Propellants
  • 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.

Associated Stages
  • 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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