Lox/LH2 propellant rocket stage. Loaded/empty mass 5,900,000/530,000 kg. Thrust 62,270.00 kN. Vacuum specific impulse 320 seconds. Length with extendible nozzle deployed 87 m. Diameter of extended nozzle 30 m. Total mass, specific impulse estimated from booster performance figures.
Cost $ : 10.000 million.
Status: Study.
Gross mass: 5,900,000 kg (13,000,000 lb).
Unfuelled mass: 530,000 kg (1,160,000 lb).
Height: 44.00 m (144.00 ft).
Diameter: 21.50 m (70.50 ft).
Span: 23.00 m (75.00 ft).
Thrust: 62,270.00 kN (13,998,850 lbf).
Specific impulse: 320 s.
Burn time: 260 s.
More... - Chronology...
Associated Countries
Associated Engines
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Sea Dragon-2 Aerojet lox/lh2 rocket engine. 62,270 kN. Design, 1962. Truax pressure fed design. Diameter of extended nozzle 30 m. Specific impulse estimated from booster performance figures. Isp=320s. More...
Associated Propellants
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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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