Lox/LH2 propellant rocket stage. Loaded/empty mass 170,800/12,700 kg. Thrust 1,114.00 kN. Vacuum specific impulse 430 seconds. Chamber pressure 108 bar; expansion ratio 45.0; propellant mix ratio 5.3.
Cost $ : 65.000 million.
More... - Chronology...
Gross mass: 170,800 kg (376,500 lb).
Unfuelled mass: 12,700 kg (27,900 lb).
Height: 30.50 m (100.00 ft).
Diameter: 5.46 m (17.91 ft).
Span: 5.46 m (17.91 ft).
Thrust: 1,114.00 kN (250,437 lbf).
Specific impulse: 430 s.
Specific impulse sea level: 340 s.
Burn time: 589 s.
Number: 57 .
Vulcain SEP, Ottobrunn lox/lh2 rocket engine. 1075 kN. In production. Isp=431s. Powered the cryogenic core stage of Ariane 5. 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...
Lox/LH2 Liquid oxygen was the earliest, cheapest, safest, and eventually the preferred oxidiser for large space launchers. Its main drawback is that it is moderately cryogenic, and therefore not suitable for military uses where storage of the fuelled missile and quick launch are required. Liquid hydrogen was identified by all the leading rocket visionaries as the theoretically ideal rocket fuel. It had big drawbacks, however - it was highly cryogenic, and it had a very low density, making for large tanks. The United States mastered hydrogen technology for the highly classified Lockheed CL-400 Suntan reconnaissance aircraft in the mid-1950's. The technology was transferred to the Centaur rocket stage program, and by the mid-1960's the United States was flying the Centaur and Saturn upper stages using the fuel. It was adopted for the core of the space shuttle, and Centaur stages still fly today. More...
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