The invention provides an aircraft body leading edge structure based on a carbon foam material, a preparation method of the aircraft body leading edge structure and an aircraft. The engine body front edge structure based on the carbon foam material comprises a skin piece, a heat conduction piece, a packaging piece and a heat dissipation piece. The skin part forms the outline of the aircraft body front edge structure and forms a containing space; the heat conduction part is made of a carbon foam material, is attached to the inner wall surface of the skin part and is filled in the accommodating space; the packaging piece is attached to the heat conduction piece and seals an opening, opposite to the front edge structure of the machine body, of the containing space. The heat dissipation piece is located in the containing space between the skin piece and the packaging piece, arranged in the heat conduction piece in a penetrating mode and used for introducing high-temperature gas, so that when the high-temperature gas flows through the heat conduction piece, heat is transmitted to the outer surface of the skin piece through the heat conduction piece. The engine body leading edge structure based on the heat conduction piece made of the carbon foam material can effectively improve the conduction efficiency of heat from high-temperature gas on the structure and remarkably improve the heat energy utilization rate, and meanwhile is simple in structure, convenient to manufacture and reliable and universal in system.
本公开提供了一种基于碳泡沫材料的机体前缘结构及其制备方法、飞行器。该基于碳泡沫材料的机体前缘结构包括蒙皮件、导热件、封装件和散热件。蒙皮件构成机体前缘结构的轮廓,形成容纳空间;导热件由碳泡沫材料构成,贴合蒙皮件的内壁面上,填充在容纳空间中;封装件贴合在导热件上,封闭容纳空间相对机体前缘结构的开口;散热件位于蒙皮件和封装件之间的容纳空间中,并穿设在导热件中,用于引入高温气体,使得高温气体在流经导热件时,将热量经导热件传递到蒙皮件的外表面上。基于碳泡沫材料的导热件的机体前缘结构,可以有效提高来自高温气体的热量在结构上的传导效率,显著提高热能利用率,同时结构简单且便于制造,系统可靠通用。
Aircraft body leading edge structure based on carbon foam material, preparation method of aircraft body leading edge structure and aircraft
基于碳泡沫材料的机体前缘结构及其制备方法、飞行器
2023-04-18
Patent
Electronic Resource
Chinese
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