Lox/LH2 propellant rocket stage. Loaded/empty mass 15,000/2,000 kg. Thrust 147.00 kN. Vacuum specific impulse 425 seconds.
Cost $ : 10.000 million.
Status: Test 1962.
More... - Chronology...
Gross mass: 15,000 kg (33,000 lb).
Unfuelled mass: 2,000 kg (4,400 lb).
Height: 10.00 m (32.00 ft).
Diameter: 3.00 m (9.80 ft).
Span: 3.00 m (9.80 ft).
Thrust: 147.00 kN (33,046 lbf).
Specific impulse: 425 s.
Specific impulse sea level: 306 s.
Burn time: 363 s.
Truax LH2 Aerojet lox/lh2 rocket engine. 147.1 kN. Test 1962. Used in Sea Horse-2. Isp=425s. More...
Associated Launch Vehicles
Sea Horse American sea-launched test vehicle. The second phase of Sea Launch was to demonstrate the concept on a larger scale, with a rocket with a complex set of guidance and control systems. Sea Horse used one of 39 surplus Corporal missiles that Truax obtained from the Army and successfully demonstrated ignition in the ocean of a rocket stage. 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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