Lox/LH2 propellant rocket stage. Loaded/empty mass 770,835/63,480 kg. Thrust 8,265.26 kN. Vacuum specific impulse 425 seconds. Version for Saturn C-8.
No Engines: 8.
Status: Study 1960.
More... - Chronology...
Gross mass: 770,835 kg (1,699,400 lb).
Unfuelled mass: 63,480 kg (139,940 lb).
Height: 42.68 m (140.02 ft).
Diameter: 10.06 m (33.00 ft).
Span: 10.06 m (33.00 ft).
Thrust: 8,265.26 kN (1,858,104 lbf).
Specific impulse: 425 s.
Specific impulse sea level: 306 s.
Burn time: 338 s.
J-2 Rocketdyne lox/lh2 rocket engine. 1033.1 kN. Study 1961. Isp=421s. Used in Saturn IVB stage in Saturn IB and Saturn V, and Saturn II stage in Saturn V. Gas generator, pump-fed. First flight 1966. More...
Associated Launch Vehicles
Saturn C-8 American orbital launch vehicle. The largest member of the Saturn family ever contemplated. Designed for direct landing of Apollo command module on moon. Configuration used eight F-1 engines in the first stage, eight J-2 engines in the second stage, and one J-2 engine in the third stage. Distinguishable from Nova 8L in use of J-2 engines instead of M-1 engines in second 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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