Lox/LH2 propellant rocket stage. Loaded/empty mass 799,537/131,519 kg. Thrust 10,290.00 kN. Vacuum specific impulse 442 seconds. Faget Configuration
Cost $ : 20.000 million. No Engines: 4.
Status: Study 1970.
More... - Chronology...
Gross mass: 799,537 kg (1,762,677 lb).
Unfuelled mass: 131,519 kg (289,949 lb).
Height: 61.89 m (203.05 ft).
Diameter: 5.08 m (16.66 ft).
Span: 42.99 m (141.04 ft).
Thrust: 10,290.00 kN (2,313,280 lbf).
Specific impulse: 442 s.
Specific impulse sea level: 392 s.
Burn time: 277 s.
Associated Launch Vehicles
Shuttle DC-3 American winged orbital launch vehicle. Marshall Spaceflight Center shuttle concept of April 1970 using Faget low cross range stub-winged booster and orbiter. 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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