| 摘要 |
A propulsion system for a flying craft uses an air and water fuel source to provide propulsion thrust. The system includes two steam generating units, one attached directly to a compact turbine and the other connected to a compressor. The compressor compresses the steam from the latter steam generator, including excess steam from the turbine generator, and pumps it to a super-heated steam compression chamber. At the same time, the turbine generator powers another compressor to take in air from the atmosphere and pumps it into a super chilled compression chamber. After both the compressed super-heated steam and the compressed super chilled air have attained required pressure, volume and temperature, both gases are fed into an expansion chamber under appropriate control. The expansion chamber operates as a rocket booster and is equipped with an exhaust system made up of a main nozzle and several auxiliary thrust vectoring nozzles. Reactionary forces within the expansion chamber, caused by expansion of the chilled steam, cause thrust and generated heat. The generated heat heats the chilled compressed air within the gas expansion chamber, causing expansion of the chilled air, providing further thrust. The exhaust system controls exiting of the expanding gases to control and vector the thrust. Preferably, the heat source for the system is one or more nuclear reactors.
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