Encyclopedia Astronautica

Credit: Yuzhnoye
Yuzhnoye N2O4/UDMH rocket engine. 5.9 kN. Upper stages. Developed 1972. Isp=320s. Engine used a novel scheme combining an existing proven combustion chamber but using a pneumatic pump for propellant supply.

This allowed:

  • Multiple restarts (up to 15)
  • Precision throttling of thrust to any value between 200 and 600 kgf simply by controlling the pneumatic pump, without the need for an elaborate control system with various pressure and flow sensors
  • Reduction in the gas needed for propellant feed was reduced by 1.4 to 1.7 times compared to conventional methods
  • High accuracy of mixture ratio maintenance
  • Stage tanks operarted under low pressure
  • Thrust increase of existing thrust chambers by 1.4 to 1.8 x
  • Use of proven components from mass-produced engines such as combustion chamber, pneumatic pump elements, and control units

Application: Upper stages.


Throttled thrust(vac): 1.960 kN (441 lbf). Engine: 30 kg (66 lb). Oxidizer to Fuel Ratio: 2. Restarts: 15.

Status: Developed 1972.
Thrust: 5.90 kN (1,326 lbf).
Specific impulse: 320 s.
Burn time: 1,500 s.
First Launch: Developed late 1960's.

More... - Chronology...

Associated Countries
See also
Associated Manufacturers and Agencies
  • Yuzhnoye Ukrainian manufacturer of rockets, spacecraft, and rocket engines. Yangel Design Bureau, Dnepropetrovsk, Ukraine. More...

Associated Propellants
  • N2O4/UDMH Nitrogen tetroxide became the storable liquid propellant of choice from the late 1950's. 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...

  • Yuzhnoye Company Web Site, Web Address when accessed: here.

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