Lox/LH2 rocket stage. Mass 257,778 kg (568,303 lb).
Cost $ : 10.000 million. No Engines: 0.
Status: Study 1966.
More... - Chronology...
Gross mass: 257,778 kg (568,303 lb).
Unfuelled mass: 12,971 kg (28,596 lb).
Height: 25.00 m (82.00 ft).
Diameter: 8.00 m (26.20 ft).
Span: 8.00 m (26.20 ft).
Specific impulse: 455 s.
Specific impulse sea level: 355 s.
Burn time: 209 s.
None Indicates that the stage shown is a propellant tank. The engine on another stage is drawing propellants from this tank. Performance shown is for that of the engine on the other stage. First flight 1964. More...
Associated Launch Vehicles
Starclipper American winged orbital launch vehicle. Lockheed ILRV design created for the USAF in 1966. X-24B lifting body configuration orbiter with linear aerospike engine and wrap-around drop tank. Related to Lockheed Shuttle LS200 proposal. 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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