Lox/LH2 propellant rocket stage. Loaded/empty mass 57,000/7,000 kg. Thrust 490.00 kN. Vacuum specific impulse 440 seconds. Additionally 4 vernier Lox/LH2 engines with a total thrust of 4600 kgf and a storable engine package for stage propellant ullage and restart.
Status: Design 1992.
More... - Chronology...
Gross mass: 57,000 kg (125,000 lb).
Unfuelled mass: 7,000 kg (15,400 lb).
Height: 10.00 m (32.00 ft).
Diameter: 4.50 m (14.70 ft).
Span: 4.50 m (14.70 ft).
Thrust: 490.00 kN (110,150 lbf).
Specific impulse: 440 s.
Burn time: 430 s.
Associated Launch Vehicles
Project 921 In 1992 Xiandong Bao of the Shanghai Astronautics Bureau revealed plans for a modular family of modern rockets to support future Chinese manned space activities. The entire family would be based on a Lox/Kerosene booster stage of 306 tonnes mass, and a Lox/LH2 upper stage of 57 tonnes mass. 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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