The invention relates to the technical field of unmanned aerial vehicle structure design, and discloses an unmanned aerial vehicle composite material leading edge structure and a manufacturing method thereof, and the unmanned aerial vehicle composite material leading edge structure comprises a front beam, a partition plate, a core material and a leading edge skin. The partition plate, the core material, the front beam and the front edge skin are fixed together through secondary glue joint to form the composite airfoil front edge. All-composite material parts are adopted and formed through a composite material secondary cementing process, and the structure has the advantages of being excellent in bird impact resistance, simple in structure, light in weight, easy to assemble, short in manufacturing period, low in cost and the like.

    本发明涉及无人机结构设计技术领域,公开了一种无人机复合材料前缘结构及其制造方法,其包括:前梁、隔板、芯材和前缘蒙皮。隔板、芯材、前梁及前缘蒙皮通过二次胶接固定在一起,形成复合材料翼面前缘。本发明采用全复合材料零件利用复合材料二次胶接工艺成型,该结构不仅具有优异的抗鸟撞能力,而且结构简单、重量轻、装配简单、制造周期短、成本低等特点。


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    Titel :

    Composite material leading edge structure of unmanned aerial vehicle and manufacturing method of composite material leading edge structure


    Weitere Titelangaben:

    一种无人机复合材料前缘结构及其制造方法


    Beteiligte:
    FAN YU (Autor:in) / YANG GAO (Autor:in) / LI MINGSHENG (Autor:in) / WANG XINNIAN (Autor:in) / MAO QINGSONG (Autor:in) / REN ALONG (Autor:in)

    Erscheinungsdatum :

    14.03.2025


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / B23P Sonstige Metallbearbeitung , OTHER WORKING OF METAL / B29C Formen oder Verbinden von Kunststoffen , SHAPING OR JOINING OF PLASTICS / B64U



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