Lox/LH2 propellant rocket stage. Loaded/empty mass 13,600/3,100 kg. Thrust 274.00 kN. Vacuum specific impulse 452 seconds.
No Engines: 2.
Status: Design 1999.
More... - Chronology...
Gross mass: 13,600 kg (29,900 lb).
Unfuelled mass: 3,100 kg (6,800 lb).
Height: 13.60 m (44.60 ft).
Diameter: 2.40 m (7.80 ft).
Span: 9.25 m (30.34 ft).
Thrust: 274.00 kN (61,597 lbf).
Specific impulse: 452 s.
Specific impulse sea level: 340 s.
Burn time: 167 s.
HIMES Mitsubishi lox/lh2 rocket engine. 137.3 kN. Design 1999. Isp=452s. Used on H-2 HIMES launch vehicle. More...
Associated Launch Vehicles
H-2 HIMES Japanese orbital launch vehicle. Concept of H-2 augmented with Liquid-Air Cycle Engine boosters and advanced HIMES 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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