Encyclopedia Astronautica
Vexin A


SEP N2O4/UDMH rocket engine. 68.6 kN. Isp=277s. Used on Europa launch vehicle. First flight 1964.

Thrust (sl): 59.500 kN (13,376 lbf). Thrust (sl): 6,065 kgf. Engine: 175 kg (385 lb). Thrust to Weight Ratio: 40.

Unfuelled mass: 175 kg (385 lb).
Diameter: 0.50 m (1.64 ft).
Thrust: 68.60 kN (15,422 lbf).
Specific impulse: 277 s.
Specific impulse sea level: 240 s.
Burn time: 96 s.
Number: 44 .

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Associated Countries
See also
Associated Launch Vehicles
  • Europa European orbital launch vehicle. Europe's first space launcher. The first stage was a British Blue Streak IRBM, the second stage the French Coralie, and the third stage the German Astris. All orbital launch attempts failed due to unreliability of the third stage. The project was cancelled after withdrawal of British support and replaced by the Ariane. 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...

Associated Stages
  • Europa-2 N2O4/UDMH propellant rocket stage. Loaded/empty mass 11,894/2,099 kg. Thrust 274.00 kN. Vacuum specific impulse 277 seconds. More...

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