Encyclopedia Astronautica
Ariane H8

Lox/LH2 propellant rocket stage. Loaded/empty mass 9,687/1,457 kg. Thrust 61.67 kN. Vacuum specific impulse 443 seconds. High energy upper stage for Ariane booster series.

Cost $ : 11.600 million.

AKA: H- 8.
Status: Out of production.
Gross mass: 9,687 kg (21,356 lb).
Unfuelled mass: 1,457 kg (3,212 lb).
Height: 10.23 m (33.56 ft).
Diameter: 2.66 m (8.72 ft).
Span: 2.66 m (8.72 ft).
Thrust: 61.67 kN (13,865 lbf).
Specific impulse: 443 s.
Burn time: 563 s.
Number: 25 .

More... - Chronology...

Associated Countries
Associated Engines
  • HM7-A SEP, Ottobrunn lox/lh2 rocket engine. 61.7 kN. Development begun 1973. Out of production. Isp=443s. Used on Ariane 1 launch vehicle. First flight 1979. More...

Associated Launch Vehicles
  • Ariane 1 French orbital launch vehicle. First version of the Ariane launch vehicle. More...

Associated Propellants
  • 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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