Lox/LH2 propellant rocket stage. Loaded/empty mass 12,000/1,600 kg. Thrust 62.70 kN. Vacuum specific impulse 446 seconds.
Cost $ : 12.000 million. Cost $ : 12.000 million.
More... - Chronology...
Status: Retired 2003.
Gross mass: 12,000 kg (26,000 lb).
Unfuelled mass: 1,600 kg (3,500 lb).
Height: 11.53 m (37.82 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: 731 s.
Number: 214 .
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
Ariane 3 French orbital launch vehicle. Four stage vehicle consisting of 2 x PAP solid rocket boosters + Ariane 2 core. More...
Ariane 2 French orbital launch vehicle. Basic three stage vehicle without solid rocket motor strap-ons. Payload to geosynchronous transfer orbit was 2,175 kg. More...
Ariane 44LP French orbital launch vehicle. Ariane 4 with 2 liquid rocket + 2 solid rocket strap-ons. More...
Ariane 44L French orbital launch vehicle. Ariane 4 with 4 liquid rocket strap-ons. More...
Ariane 40 French orbital launch vehicle. 3 stage core vehicle with original Ariane H10 upper stage. A fully fueled Ariane core cannot lift off the ground without strap-on liquid or solid motors. When Ariane 4 is launched in this configuration, the propellant tanks of the first and second stages are not completely filled. More...
Ariane 42P French orbital launch vehicle. Ariane 4 with 2 solid rocket strap-ons. More...
Ariane 44P French orbital launch vehicle. Ariane 4 with 4 solid rocket strap-ons. More...
Ariane 42L French orbital launch vehicle. Ariane 4 with 2 liquid rocket strap-ons. 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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