Lox/LH2 propellant rocket stage. Loaded/empty mass 614,000/38,000 kg. Thrust 10,228.00 kN. Vacuum specific impulse 420 seconds.
No Engines: 7.
Status: Study 1960.
More... - Chronology...
Gross mass: 614,000 kg (1,353,000 lb).
Unfuelled mass: 38,000 kg (83,000 lb).
Height: 23.80 m (78.00 ft).
Diameter: 12.20 m (40.00 ft).
Span: 12.20 m (40.00 ft).
Thrust: 10,228.00 kN (2,299,345 lbf).
Specific impulse: 420 s.
Specific impulse sea level: 150 s.
Burn time: 228 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
Nova B American heavy-lift orbital launch vehicle. Convair/Ehricke Nova design using standard tank/engine modules of 4.9 m diameter in both first and second stages; 6 F-1 engine/modules in first stage, 6 J-2 engine/modules in second stage. More...
Nova D American nuclear orbital launch vehicle. General Dynamics Nova vehicle using Nova B as first two stages, nuclear spacecraft with jettisonable tanks as upper 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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