N2O4/MMH propellant rocket stage. Loaded/empty mass 12,500/2,700 kg. Thrust 27.40 kN. Vacuum specific impulse 324 seconds. Storable propellant, restartable upper stage for use with Ariane 5. Chamber pressure 10 bar; expansion ratio 83.0; propellant mix ratio 2.05. Empty mass without VEB payload fairing support ring and avionics is 1200 kg.
Cost $ : 6.000 million.
More... - Chronology...
Gross mass: 12,500 kg (27,500 lb).
Unfuelled mass: 2,700 kg (5,900 lb).
Height: 3.36 m (11.02 ft).
Diameter: 3.96 m (12.99 ft).
Span: 5.46 m (17.91 ft).
Thrust: 27.40 kN (6,160 lbf).
Specific impulse: 324 s.
Burn time: 1,100 s.
Number: 48 .
Aestus Friedrichshafen N2O4/MMH rocket engine. 29 kN. In production. Isp=324s. Upper stage engine for Ariane 5 developed 1988 - 1995. Original version could not be restarted; version for EPS L10 stage for Ariane 5V allowed multiple restarts. First flight 1996. More...
L7 MBB N2O4/MMH rocket engine. 27.4 kN. In Production. Isp=320s. Used on Ariane 5 launch vehicle. First flight 1996. More...
Associated Launch Vehicles
Ariane 5G French orbital launch vehicle. Initial version of the Ariane 5, a bit too large for the main commercial geosynchronous communications satellite payloads. More...
N2O4/MMH Nitrogen tetroxide became the storable liquid propellant of choice from the late 1950's. Monomethylhydrazine (CH3NHNH2) is a storable liquid fuel that found favour in the United States for use in orbital spacecraft engines. Its advantages in comparison to UDMH are higher density and slightly higher performance. More...
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