MBB N2O4/MMH rocket engine. 27.4 kN. In Production. Isp=320s. Used on Ariane 5 launch vehicle. First flight 1996.
Engine: 110 kg (240 lb). Chamber Pressure: 10.35 bar. Area Ratio: 83.31. Thrust to Weight Ratio: 25.4545454545455. Oxidizer to Fuel Ratio: 2.05. Coefficient of Thrust vacuum: 1.72266671908665.
Status: In Production.
More... - Chronology...
Unfuelled mass: 110 kg (240 lb).
Height: 2.19 m (7.17 ft).
Diameter: 3.96 m (12.99 ft).
Thrust: 27.40 kN (6,160 lbf).
Specific impulse: 320 s.
Burn time: 810 s.
Number: 4 .
Associated Launch Vehicles
Ariane 5 French orbital launch vehicle. The Ariane 5 was a completely new design, unrelated to the earlier Ariane 1 to 4. It consisted of a single-engine Lox/LH2 core stage flanked by two solid rocket boosters. Preparatory work began in 1984. Full scale development began in 1988 and cost $ 8 billion. The design was sized for the Hermes manned spaceplane, later cancelled. This resulted in the booster being a bit too large for the main commercial payload, geosynchronous communications satellites. As a result, development of an uprated version capable of launching two such satellites at a time was funded in 2000. More...
Associated Manufacturers and Agencies
MBB German manufacturer of rockets, spacecraft, and rocket engines. Messerschmitt-Bolkow-Blohm GmBh, Munich, Germany. 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...
Ariane 5-2 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. More...
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