An apparatus and method for an actuator system to modify an adaptive flap of an aircraft wing. The system may include a drive rod extending from a nose portion of the flap to an interior thereof. A bell crank may be attached to the interior and configured to receive an end of the drive rod. A pivot disposed opposite of the drive rod may couple the bell crank to a mount fixed to a lower surface of a trailing edge portion of the flap. A skin overlap may be configured to allow the lower surface of the trailing edge portion to slide adjacent to a lower surface of a remaining portion of the flap under the action of the drive rod. A bumper may be disposed within the aircraft wing and configured to exert a continuous force on the drive rod when the flap is moved to a retracted state.


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    Titel :

    Actuator for Adaptive Airfoil


    Beteiligte:
    DAVIS EDWARD (Autor:in)

    Erscheinungsdatum :

    2019-05-23


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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