Encyclopedia Astronautica

Credit: Yuzhnoye
Yuzhnoye N2O4/UDMH rocket engine. 23.250 kN. Apogee stage. Developed 1983-. Isp=325s. In development in 1996. One main and an unknown number of control thrusters. 23.25 + 0.03 kN. Chamber pressure 91.5 / 6.9 bar. Specific impulse 325 / 230 sec.

Burn time 1600 / 7200 sec. Oxidizer to fuel ratio 2.2 / 1.6

Application: Apogee stage.


Chambers: 1 + x. Engine: 203 kg (447 lb). Chamber Pressure: 91.50 bar. Thrust to Weight Ratio: 11.67. Oxidizer to Fuel Ratio: 2.2.

Status: Developed 1983-.
Unfuelled mass: 203 kg (447 lb).
Height: 1.10 m (3.60 ft).
Diameter: 2.35 m (7.70 ft).
Thrust: 23.25 kN (5,227 lbf).
Specific impulse: 325 s.
Burn time: 1,600 s.
First Launch: 1983-.

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Associated Countries
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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...

  • Shnyakin, V N, Shidkostnye Raketye Dvigateli - Opisanie i Osnovnye Tekhnicheskie Dannye, GKB Yuzhnoe "Yangel", Dnepropetrovsk 1996 via Dietrich Haeseler.

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