The invention discloses an aircraft leading edge sealing structure. The component comprises a sealing rubber profile, a pressing plate, a fixed trailing edge skin, a control surface front edge skin and a reinforcing partition plate. Wherein the sealing rubber profile is herringbone, the height and the width of the sealing rubber profile are gradually changed along the spanwise dimension, and the sealing rubber profile is fixed on the fixed trailing edge skin through the pressing plate; the fixed trailing edge skin is of a honeycomb sandwich structure, and the joint of the fixed trailing edge skin and the rubber profile is of a laminated plate structure; the leading edge skin is in a hook shape and is provided with a notch. The reinforcing partition plate is in an L shape and reinforces the opening area of the front edge skin.

    本发明公开了一种飞机前缘密封结构。其中,该部件包括:密封橡胶型材、压板、固定后缘蒙皮、舵面前缘蒙皮和加强隔板。其中:密封橡胶型材为人字形,高度和宽度沿展向尺寸渐变,通过压板固定在固定后缘蒙皮上;固定后缘蒙皮为蜂窝夹芯结构,与橡胶型材连接部位为层合板结构;前缘蒙皮为弯钩形状,并带有缺口;加强隔板为L型,对前缘蒙皮开口区域进行加强。


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    Titel :

    Aircraft leading edge sealing structure


    Weitere Titelangaben:

    一种飞机前缘密封结构


    Beteiligte:
    WANG ZHIGANG (Autor:in) / FU SHUO (Autor:in) / WANG LIPING (Autor:in) / YUAN BO (Autor:in)

    Erscheinungsdatum :

    08.03.2024


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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