A wing used for an aircraft includes a configuration member formed of a composite material. The configuration member is divided into a plurality of regions along a surface thereof. The plurality of regions include a first region formed of the composite material of a high strength type, and a second region formed of the composite material of a high elasticity type having higher rigidity than the high strength type. The first region includes any region closest to a wing end side out of the plurality of regions, and the second region includes a region closest to the wing end side and a trailing edge side out of the plurality of regions.


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    Titel :

    Wing and wing design method


    Beteiligte:
    NOMURA TAKAYUKI (Autor:in) / KODAMA SATOSHI (Autor:in) / YUMITORI TAKAAKI (Autor:in) / TAKAGI KIYOKA (Autor:in) / SHITANI TOORU (Autor:in) / ABE TOSHIO (Autor:in)

    Erscheinungsdatum :

    2022-06-21


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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