SEP N2O4/UDMH rocket engine. 75.4 kN. Out of production. Isp=251s. Used on Diamant launch vehicle. First flight 1965.
Thrust (sl): 66.400 kN (14,927 lbf). Thrust (sl): 6,768 kgf. Engine: 192 kg (423 lb). Thrust to Weight Ratio: 40.0364583333333.
Status: Out of production.
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Unfuelled mass: 192 kg (423 lb).
Diameter: 0.34 m (1.10 ft).
Thrust: 75.40 kN (16,951 lbf).
Specific impulse: 251 s.
Specific impulse sea level: 221 s.
Burn time: 100 s.
Number: 16 .
Associated Launch Vehicles
Diamant French orbital launch vehicle. In December 1961 France decided to demonstrate an indigenous satellite-launch capability, using stages in development for its ballistic missile program. Following careful evolutionary development, Diamant was successful on its first attempt in 1965. Improved versions were flown over the next ten years. 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...
Diamant-1 N2O4/UDMH propellant rocket stage. Loaded/empty mass 14,685/1,946 kg. Thrust 301.55 kN. Vacuum specific impulse 251 seconds. More...
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