The leading edge torque box of a wing tip device includes a composite skin, at least one composite internal component, and an interior containing two or more cavities each configured to receive one of a plurality of mandrels such that a pair of the plurality of mandrels are located on opposite sides of one of the at least one internal component. The pair of the plurality of mandrels expand to compact composite layups of the composite skin against an outer mold line tool while simultaneously compacting composite layups of the one of the at least one internal component between the pair of the plurality of mandrels. The plurality of mandrels are removable by solubilization, which may facilitate removal of the plurality of mandrels from the leading edge torque box after the leading edge torque box is cured.

    La présente invention concerne un dispositif (107) de bout d'aile d'aéronef, qui comprend un caisson de torsion de bord avant, monolithique et unifié, constitué d'un matériau renforcé en fibre de matrice polymère. Le caisson de torsion de bord avant comprend un revêtement (160), qui délimite une surface de ligne de moule extérieur, continue et ininterrompue, qui s'étend vers l'arrière, depuis un bord avant d'ailette de bout d'aile, d'une distance d'au moins 60 % environ d'une longueur de corde locale. Le caisson de torsion (172) de bord avant comprend en outre au moins un composant interne (162), qui s'étend entre des surfaces internes opposées du revêtement et qui y est intégré.


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    Title :

    NATURAL LAMINAR FLOW WINGTIP


    Additional title:

    BOUT D'AILE A ECOULEMENT LAMINAIRE NATUREL


    Contributors:

    Publication date :

    2019-03-05


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



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