Lox/LH2 propellant rocket stage. Loaded/empty mass 500,000/45,000 kg. Thrust 4,457.10 kN. Vacuum specific impulse 425 seconds. Part of launch vehicle proposed by Martin as alternative to NLS. All figures estimated based on 1,000,000 lb thrust single engine.
Status: Study 1988.
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Gross mass: 500,000 kg (1,100,000 lb).
Unfuelled mass: 45,000 kg (99,000 lb).
Height: 60.00 m (196.00 ft).
Diameter: 6.00 m (19.60 ft).
Span: 6.00 m (19.60 ft).
Thrust: 4,457.10 kN (1,001,996 lbf).
Specific impulse: 425 s.
Specific impulse sea level: 354 s.
Burn time: 420 s.
PW 1000000 lb LH2 Pratt and Whitney lox/lh2 rocket engine. 4457 kN. Study 1988. Part of launch vehicle proposed by Martin as alternative to NLS. All figures estimated based on 1,000,000 lb thrust single engine. Isp=425s. More...
Associated Launch Vehicles
Titan 5 American orbital launch vehicle. Proposed Titan upgrade with cryogenic core as replacement for NLS. 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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