Encyclopedia Astronautica

Credit: Boeing / Rocketdyne
Rocketdyne N2O4/UDMH rocket engine. 0.205 kN. SE-5-2/-3. Agena Auxiliary. Pressure-fed. SE-5-2 four engines in satellite system. SE-5-3 two engines for Agena auxiliary propuslion. Isp=272s. First flight 1963.

Application: SE-5-2/-3.

Propellant Formulation: N2O4/Hydrazine(75%)-MMH(25%).

Thrust: 205 N (46 lbf).
Specific impulse: 272 s.
First Launch: 1962.

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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...

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