An airfoil body is provided for an aircraft which includes a first skin, a second skin, a plurality of first stiffeners and a plurality of second stiffeners. The first stiffeners are configured from or otherwise include first stiffener composite material. The first stiffeners extends widthwise between and are connected to the first skin and the second skin. Each of the first stiffeners has a first stiffener longitudinal centerline that extends spanwise along the first skin and the second skin. The second stiffeners are configured from or otherwise include second stiffener composite material. The second stiffeners extend widthwise between and are connected to the first skin and the second skin. Each of the second stiffeners has a second stiffener longitudinal centerline that extends lengthwise along the first skin and the second skin.


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    Titel :

    Composite airfoil for an aircraft


    Beteiligte:
    CHEUNG ALAN K (Autor:in) / DAVIS JENNIFER (Autor:in) / DSOUZA PAUL (Autor:in) / ABILLE GERALD S (Autor:in)

    Erscheinungsdatum :

    15.08.2023


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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