Lox/LH2 propellant rocket stage. Loaded/empty mass 10,489,000/626,000 kg. Thrust 156,876.00 kN. Vacuum specific impulse 443 seconds. Operational date would have been April 1975. SSTO - payload 1,042,000 lbs.
No Engines: 24.
Status: Study 1963.
More... - Chronology...
Gross mass: 10,489,000 kg (23,124,000 lb).
Unfuelled mass: 626,000 kg (1,380,000 lb).
Height: 75.90 m (249.00 ft).
Diameter: 24.40 m (80.00 ft).
Span: 26.20 m (85.90 ft).
Thrust: 156,876.00 kN (35,267,127 lbf).
Specific impulse: 443 s.
Specific impulse sea level: 379 s.
Burn time: 268 s.
HP-1 Notional lox/lh2 rocket engine. 6536 kN. Study 1963. Operational date would have been December 1974. Isp=451s. Used in Martin Nova studies MM 24G, MM 33. More...
Associated Launch Vehicles
Nova MM 33 American heavy-lift orbital launch vehicle. Nova single stage to orbit design with 24 new high pressure LH2/Lox engines in the first stage in a plug nozzle arrangement. Operational date would have been April 1975. 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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