N2O4/UDMH propellant rocket stage. Loaded mass 2,200 kg. Thrust 156.00 kN.
Status: Retired 1965.
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Gross mass: 2,200 kg (4,800 lb).
Height: 4.60 m (15.00 ft).
Diameter: 0.80 m (2.62 ft).
Thrust: 156.00 kN (35,070 lbf).
Burn time: 44 s.
Number: 4 .
Associated Launch Vehicles
Topaze VE111L French test vehicle. The VE111L (long) used the stretched NA803 motor. The VE111L was successfully demonstrated the thrust vectoring concept over a longer burn period. The last two flights were VE111LG configuration, equipped with all-up inertial navigation systems. More...
Associated Manufacturers and Agencies
SEREB French manufacturer of rocket engines and rockets. SEREB, France. More...
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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