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.


    Access

    Download


    Export, share and cite



    Title :

    Flap actuator mechanism


    Contributors:

    Publication date :

    2021-08-17


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



    FLAP ACTUATOR MECHANISM

    TSAI KEVIN R | European Patent Office | 2021

    Free access

    Linear Actuator Driven Flap Mechanism

    BLOCK SAMUEL L / TSAI KEVIN R | European Patent Office | 2024

    Free access

    Linear actuator driven flap mechanism

    BLOCK SAMUEL L / TSAI KEVIN R | European Patent Office | 2025

    Free access

    FLAP ACTUATOR

    WINTER ANDREAS | European Patent Office | 2024

    Free access

    Flap actuator

    FRICK JOERN / GAILE ANTON / WEIXLER FRANZ | European Patent Office | 2017

    Free access