| 摘要 |
An ultra hypersonic aircraft having aerodynamic heat transferring pipes forming an airframe structure is shown. The heat transformer pipes include a high pressure steam generator located at the forward section thereof and a low pressure steam condensator located at the rearward section thereof. Low pressure water is circulated between the rearward section and the forward section for heat balancing of the air frame structure and for operating the room air conditioning system of an aircraft. A steam pressure reactant turbine, which drives an electric generator, is used as a boundary between the high and low pressure steam sections. The electric generator provided electrical and power supply for the infrared or arc heaters, and electric heaters recessed in the ceiling and wall panels of an acrodynamic lift-thrust generating channel for back-heating of the turbo-ram oval thrust stream in the thrust generating channel of a hypersonic aircraft. The thrust generating channel steam cooled ram constriction vane diffuser as the air intake of a turbo-ram induction jet engine and includes a steam cooled ignition-combustion chamber inductor vanes of a ram induction jet oval thrust nozzle, oval thrust nozzle located forward of a steam cooled vacuum cell wing for enhancing the vacuum induction thrust force generated on the wing and an aerodynamic heat sink is used to transform the thrust power generation.
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