Encyclopedia Astronautica

Isayev N2O4/UDMH rocket engine. 0.200 kN. In Production. Bi-propellant hypergolic (self-igniting) engine, pressure-fed. 10,000 ignitions Isp=280s.

Engine: 1.30 kg (2.80 lb). Chamber Pressure: 15.00 bar. Area Ratio: 43. Thrust to Weight Ratio: 15.38. Oxidizer to Fuel Ratio: 1.85.

Status: In Production.
Unfuelled mass: 1.30 kg (2.80 lb).
Thrust: 200 N (40 lbf).
Specific impulse: 280 s.
Burn time: 5,000 s.

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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...

  • Haeseler, Dietrich, Visit to the museum of Chemical Machining Design Bureau, Kalinin 1998 via Dietrich Haeseler.

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