The invention discloses an aircraft electric heating leading edge structure and a manufacturing method, the leading edge structure comprises an integral structure composed of an outer skin, an inner skin, an outer insulating layer, an inner insulating layer and a heating element layer, the outer skin and the inner skin are aluminum alloy sheet metal skins, the outer insulating layer and the inner insulating layer are composite material high-temperature epoxy pre-impregnated glass cloth, and the heating element layer is made of composite material high-temperature epoxy pre-impregnated glass cloth. The heating element layer is embedded between the inner insulating layer and the outer insulating layer, the heating element layer comprises a plurality of uniformly arranged heating elements, bus bars and protective films, each heating element is woven into a rectangular silk screen structure by resistance wires, the two sides of each heating element are provided with the protective films formed by paving high-temperature epoxy pre-impregnated glass cloth, the bus bars are of a metal conductive structure, and the bus bars are of a metal conductive structure. The bus bars are used for communicating the heating elements on the two sides to form a complete communicating circuit, and the multiple heating elements and the multiple bus bars are connected to form a uniform heating element layer matched with the front edge.
一种飞机电加温前缘结构及制造方法,该前缘结构包含外蒙皮、内蒙皮、外绝缘层、内绝缘层、加温元件层组成的整体结构,所述的外蒙皮、内蒙皮为铝合金钣金蒙皮,所述的外绝缘层和内绝缘层为复合材料高温环氧预浸玻璃布,所述的加温元件层,嵌入在内、外绝缘层之间,加温元件层含有多个均匀布置的加温元件、汇流条和保护膜,每个加温元件由电阻丝编织为长方形丝网结构,其两侧设有用高温环氧预浸玻璃布铺贴形成保护膜,所述的汇流条为金属导电结构,用于联通两侧的加温元件,形成一个完整的联通电路,多个加温元件和多个汇流条连接成一个均匀的与前缘匹配的加温元件层。
Airplane electric heating leading edge structure and manufacturing method
一种飞机电加温前缘结构及制造方法
2024-04-05
Patent
Electronic Resource
Chinese
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