Provided is an electric actuator device that has a simple structure and that makes it easy to release the mechanical connection between a rudder surface and an aircraft body, such connection due to the electric actuator. An electric actuator device (10) is provided with: an electric actuator body (20) that has a first fulcrum (22) connected to a rudder surface (30) side of an aircraft and a second fulcrum (24) connected to the aircraft body side, and is driven by an electric motor such that the first fulcrum (22) and the second fulcrum (24) can be brought closer together and drawn further apart; a support member (42) for advancing/retracting between a support position at which the support member supports the first fulcrum (22) or the second fulcrum (24) thereunder, and a retracted position at which the support member is retracted from under the first fulcrum (22) or the second fulcrum (24); and a retention member (46) for retaining the first fulcrum (22) or the second fulcrum (24) when the support member (42) is located in the retracted position.


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    Title :

    ELECTRIC ACTUATOR DEVICE


    Additional title:

    ELEKTRISCHE AKTUATORVORRICHTUNG
    DISPOSITIF FORMANT ACTIONNEUR ÉLECTRIQUE


    Contributors:

    Publication date :

    2020-07-22


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



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