Lox/LH2 propellant rocket stage. Loaded/empty mass 19,501/3,000 kg. Thrust 146.80 kN. Vacuum specific impulse 444 seconds. Centaur for Shuttle payload bay. Cancelled after Challenger disaster on safety grounds.
Cost $ : 22.000 million. No Engines: 2.
Status: Out of production.
More... - Chronology...
Gross mass: 19,501 kg (42,992 lb).
Unfuelled mass: 3,000 kg (6,600 lb).
Height: 8.87 m (29.10 ft).
Diameter: 4.33 m (14.20 ft).
Span: 4.33 m (14.20 ft).
Thrust: 146.80 kN (33,002 lbf).
Specific impulse: 444 s.
Burn time: 550 s.
RL-10A-3A Pratt and Whitney lox/lh2 rocket engine. 73.4 kN. Isp=444s. Used on Centaur stage atop Atlas G, Atlas I, Atlas II, Titan 4. First flight 1984. 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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