Lox/LH2 propellant rocket stage. Loaded/empty mass 833,732/62,757 kg. Thrust 14,310.00 kN. Vacuum specific impulse 425 seconds.
Cost $ : 59.000 million. No Engines: 4.
AKA: National Launch System.
More... - Chronology...
Status: Study 1991.
Gross mass: 833,732 kg (1,838,064 lb).
Unfuelled mass: 62,757 kg (138,355 lb).
Height: 52.00 m (170.00 ft).
Diameter: 8.70 m (28.50 ft).
Span: 8.70 m (28.50 ft).
Thrust: 14,310.00 kN (3,217,010 lbf).
Specific impulse: 425 s.
Specific impulse sea level: 350 s.
Burn time: 221 s.
STME Rocketdyne lox/lh2 rocket engine. 2890 kN. Cancelled 1984. Isp=430s. Space Transportation Main Engine. Rocketdyne was teamed with Aerojet and Pratt & Whitney on the STME, which was to have powered the next generation of large launch vehicles. More...
Associated Launch Vehicles
NLS HLV American heavy-lift orbital launch vehicle. NLS Heavy Lift Version. Lower cost expendable launch vehicle studied by NASA/USAF in late 1980's. 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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