The invention relates to a support structure for an aircraft. The support structure includes a structural member having a substantially planar shape, a longitudinal axis defining a longitudinal direction, and a transverse axis orthogonal to the longitudinal axis; and a plurality of fillet holes formed along the longitudinal direction. Each fillet bore has a respective major axis having a major length and a minor axis orthogonal to the major axis, the minor axis having a minor length less than the major length. Each rounded bore is oriented such that its long axis rotates greater than 0 degrees and less than 90 degrees from the longitudinal axis of the structural member. The structural member is configured to withstand an external load acting on the structural member in a main load direction that is not parallel to the longitudinal axis or the transverse axis. Each rounded bore may be oriented such that its long axis is aligned substantially parallel to the primary load direction.

    本发明涉及用于航空器的支撑结构。该支撑结构包括:结构构件,该结构构件具有大致平面形状、限定纵向方向的纵向轴线和与所述纵向轴线正交的横向轴线;以及沿着所述纵向方向形成的多个圆角孔。每个圆角孔均具有相应的长轴和与所述长轴正交的短轴,所述长轴具有主要长度,所述短轴具有与比所述主要长度小的次要长度。每个圆角孔均被定向成使其长轴从所述结构构件的所述纵向轴线旋转大于0度且小于90度。所述结构构件被配置成用于承受在不与所述纵向轴线或所述横向轴线平行的主负载方向上作用在所述结构构件上的外部负载。每个圆角孔均可以被定向成使其长轴与所述主负载方向大致平行地对准。


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    Title :

    SUPPORT STRUCTURE FOR AIRCRAFT


    Additional title:

    用于航空器的支撑结构



    Publication date :

    2024-01-23


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



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