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.


    Zugriff

    Download


    Exportieren, teilen und zitieren



    Titel :

    Flap actuator mechanism


    Beteiligte:
    TSAI KEVIN R (Autor:in)

    Erscheinungsdatum :

    17.08.2021


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



    FLAP ACTUATOR MECHANISM

    TSAI KEVIN R | Europäisches Patentamt | 2021

    Freier Zugriff

    Linear actuator driven flap mechanism

    BLOCK SAMUEL L / TSAI KEVIN R | Europäisches Patentamt | 2025

    Freier Zugriff

    Linear Actuator Driven Flap Mechanism

    BLOCK SAMUEL L / TSAI KEVIN R | Europäisches Patentamt | 2024

    Freier Zugriff

    FLAP ACTUATOR

    WINTER ANDREAS | Europäisches Patentamt | 2024

    Freier Zugriff

    Flap actuator

    FRICK JOERN / GAILE ANTON / WEIXLER FRANZ | Europäisches Patentamt | 2017

    Freier Zugriff