An example aircraft wing includes a first skin, a second skin opposite to the first skin, and a composite spar. The composite spar includes a double-flanged spar cap, a single-flanged spar cap, a sparweb connecting the double-flanged spar cap and the single-flanged spar cap, and a tear strap. The double-flanged spar cap includes an inward-facing flange and a first outward-facing flange, and the inward-facing flange and the first outward-facing flange are integrated with the first skin during a co-curing process. The single-flanged spar cap includes a second outward-facing flange that is attached to the second skin. The tear strap is stitched to an inner side of the spar web along at least a portion of a length of the composite spar.

    示例飞行器机翼包括第一蒙皮、与第一蒙皮相对的第二蒙皮以及复合翼梁。复合翼梁包括双凸缘翼梁帽、单凸缘翼梁帽、连接双凸缘翼梁帽和单凸缘翼梁帽的翼梁腹板以及撕带。双凸缘翼梁帽包括向内凸缘和第一向外凸缘,并且在共固化过程期间,向内凸缘和第一向外凸缘与第一蒙皮成一体。单凸缘翼梁帽包括附接至第二蒙皮的第二向外凸缘。撕带沿复合翼梁的长度的至少一部分缝合至翼梁腹板的内侧。


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    Titel :

    Composite spar for aircraft wing


    Weitere Titelangaben:

    飞行器机翼的复合翼梁


    Beteiligte:
    LINTON KIM A (Autor:in) / DOBBERFUHL JAMES P (Autor:in) / BARAJA JAIME E (Autor:in) / WU HSI-YUNG T (Autor:in)

    Erscheinungsdatum :

    15.05.2020


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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