The invention provides an aircraft airfoil trailing edge, belongs to the field of aircraft design, and relates to improvements to appearance and structural forms of airfoil trailing edges. The entireairfoil trailing edge is integrally machined and formed by aluminum alloy and is installed on a main airfoil in a riveting mode, the rear end face of a trailing edge strip has consistent thickness, aboss is arranged at the front end of the trailing edge strip, the boss is embedded into the main airfoil to achieve connection and fixation, and the upper and lower curved surfaces of the trailing edge strip are tangent to the upper and lower curved surfaces of the main airfoil at connecting positions respectively. The aircraft airfoil trailing edge has the advantages of convenience in assembly and disassembly, simple appearance and structure, good rigidity, light weight, good aerodynamic performance and good manufacturability.

    本发明提供一种飞机翼面后缘,属于飞机设计领域,涉及对翼面后缘外形、结构形式的改进。本发明的整个翼面后缘由铝合金整体机加成形,用铆接的方式安装在主翼面上,后缘缘条的后端面具有一致的厚度,后缘缘条前端设置有凸台,通过凸台嵌入主翼面连接固定,后缘缘条的上下曲面与主翼面的上下曲面在连接处分别保持相切。本发明具有安装拆卸方便,外形、结构简单,刚度好,重量轻,气动性能、制造工艺性好的优点。


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    Title :

    Aircraft airfoil trailing edge


    Additional title:

    一种飞机翼面后缘


    Contributors:
    LIANG SHUANG (author) / NIE TUN (author) / ZHANG BIN (author) / ZHOU PING (author) / TENG JIE (author) / XU YIDA (author)

    Publication date :

    2020-12-18


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



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