American space tug. Study 1967. Upper stage / space tug - Boeing study, 1967. Launched by Saturn V. S-IVB with 16.5 foot stretch, 350,000 pounds propellant, 1 x 400,000 pound thrust toroidal engine.
Gross mass: 179,200 kg (395,000 lb).
More... - Chronology...
Unfuelled mass: 20,400 kg (44,900 lb).
Height: 22.82 m (74.86 ft).
Diameter: 6.61 m (21.68 ft).
Span: 6.61 m (21.68 ft).
Thrust: 1,778.90 kN (399,913 lbf).
Specific impulse: 447 s.
Toroidal 400k Notional lox/lh2 rocket engine. 1778 kN. Study 1967. Isp=447s. Used on Saturn V-3B launch vehicle. 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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