Lox/LH2 propellant rocket stage. Loaded/empty mass 12,800/1,740 kg. Thrust 62.70 kN. Vacuum specific impulse 446 seconds.
Cost $ : 12.000 million. Cost $ : 12.000 million.
More... - Chronology...
Status: Retired 1989.
Gross mass: 12,800 kg (28,200 lb).
Unfuelled mass: 1,740 kg (3,830 lb).
Height: 11.80 m (38.70 ft).
Diameter: 2.66 m (8.72 ft).
Span: 2.66 m (8.72 ft).
Thrust: 62.70 kN (14,096 lbf).
Specific impulse: 446 s.
Burn time: 750 s.
Number: 17 .
HM7-B SEP, Ottobrunn lox/lh2 rocket engine. 70 kN. Isp=447s. Increased performance version of the HM-7 engine for the Ariane 2 and 3. Combustion chamber pressure raised from 30 to 35 bar and nozzle extended. First flight 1984. More...
Associated Launch Vehicles
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...
Home - Browse - Contact
© / Conditions for Use