An actuator mechanism for a flap includes a first link having a rotary-driven end and a free end, and a second link having a forward end, a mid-portion, and an aft end. The rotary-driven end is pivotally connected to a base structure, the forward end is pivotally connected to the free end, and the aft end is connected to the flap. The actuator mechanism also includes a third link that includes a fixed end, an intermediate connector, and an end connector. The fixed end is pivotally connected to the base structure, and the intermediate connector is pivotally connected to the mid-portion of the second link. The actuator mechanism further includes a flap link including a first end pivotally connected to the end connector, and a second end pivotally connected to the flap. Rotation of the first link causes the flap to transition from a stowed to a fully deployed position.


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    Titel :

    Flap actuator mechanism


    Beteiligte:
    TSAI KEVIN R (Autor:in)

    Erscheinungsdatum :

    2021-08-17


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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