Lox/LH2 propellant rocket stage. Loaded/empty mass 1,730,803/133,514 kg. Thrust 27,422.00 kN. Vacuum specific impulse 455 seconds. High-fineness lifting-body configuration. Cross Range 2,419 km
No Engines: 9.
More... - Chronology...
Status: Study 1971.
Gross mass: 1,730,803 kg (3,815,767 lb).
Unfuelled mass: 133,514 kg (294,347 lb).
Height: 47.71 m (156.52 ft).
Diameter: 4.57 m (14.99 ft).
Span: 28.05 m (92.02 ft).
Thrust: 27,422.00 kN (6,164,711 lbf).
Specific impulse: 455 s.
Specific impulse sea level: 352 s.
Burn time: 256 s.
Associated Launch Vehicles
Shuttle LS200 American winged orbital launch vehicle. Lockheed Skunk Works alternate shuttle proposal of June 1971. X-24B lifting body orbiter with wrap-around external tank. 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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