The invention discloses an aircraft aileron composite material integral joint which comprises an upper edge strip, a lower edge strip and a web plate, a lug is arranged on the front side face of the web plate, a rib is arranged on the rear side face of the web plate, and the arrangement position of the rib corresponds to the arrangement position of the lug. The integral joint structure is prepared by adopting a composite material weaving process and RTM liquid molding, compared with a metal joint, the weight of the composite material integral joint can be reduced by more than 20% under the condition that the rigidity and the strength are equivalent, connecting fasteners of the joint and the aileron body are reduced, and meanwhile, the problem of thermal stress caused by connection of the composite aileron and the metal joint is avoided.

    本发明公开了一种飞机副翼复合材料整体接头,包括上缘条、下缘条以及腹板,所述腹板的前侧面设置有耳片,所述腹板的后侧面设置有筋条,筋条的布设位置与耳片的布设位置相对应。本发明的整体接头结构,采用编织复合材料工艺和RTM液体成型制备,相对于金属接头,复合材料整体接头在刚度和强度相当的情况下,可减重达20%以上,且减少了接头与副翼本体的连接紧固件,同时避免了复合材料副翼和金属接头连接带来的热应力问题。


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    Titel :

    Aircraft aileron composite material integral joint


    Weitere Titelangaben:

    一种飞机副翼复合材料整体接头


    Beteiligte:
    CHEN JUN (Autor:in) / HAN SICONG (Autor:in) / WANG BINTUAN (Autor:in) / LI YONGMING (Autor:in) / LI CHI (Autor:in) / YANG JIE (Autor:in)

    Erscheinungsdatum :

    2021-04-06


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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