SEP N2O4/UDMH rocket engine. 99.1 kN. Out of production. Isp=251s. Used on Diamant B launch vehicle. First flight 1970.
Thrust (sl): 87.300 kN (19,626 lbf). Thrust (sl): 8,900 kgf. Engine: 252 kg (555 lb). Thrust to Weight Ratio: 40.1111111111111.
Status: Out of production.
More... - Chronology...
Unfuelled mass: 252 kg (555 lb).
Diameter: 0.35 m (1.14 ft).
Thrust: 99.10 kN (22,279 lbf).
Specific impulse: 251 s.
Specific impulse sea level: 221 s.
Burn time: 110 s.
Number: 20 .
Associated Launch Vehicles
Diamant B French orbital launch vehicle. As a follow-on to the Diamant-A, CNES decided to evolve a more capable launch vehicle. The Diamant-B used a new first stage with 50% more propellants and 33% more thrust; the same second stage; and a fatter third stage. Six Diamant-B boosters were ordered. Originally four of these were to be used to test the Europa 2 launch vehicle's Perigee-Apogee System. These tests were cancelled and instead CNES used five of the six boosters for orbital attempts. 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 B-1 N2O4/UDMH propellant rocket stage. Loaded/empty mass 21,500/3,500 kg. Thrust 396.52 kN. Vacuum specific impulse 251 seconds. More...
Home - Browse - Contact
© / Conditions for Use