Actuator assemblies and methods of moving a control surface (50) of an aircraft utilizing the same are disclosed herein. The actuator assemblies (100) include a base structure (110) and an actuated arm (120) that is pivotally coupled to the base structure (110). The actuator assemblies (100) also include a drive assembly (130) that is operatively attached to the base structure (110) and includes an output shaft (132). The actuator assemblies (100) further include a linear actuator (140) that includes an actuator shaft (150) and an actuated body (160). The actuator shaft (150) is coupled to and configured to rotate with the output shaft (132) about an actuator shaft axis of rotation (152). The actuator assemblies (100) also include a linkage (180) that is pivotally coupled to the actuated arm (120). In addition, the linkage (180) is operatively attached to the actuated body (160) via a joint (170). The joint (170) defines a plurality of joint axes (172) of rotation that are spaced apart from the actuator shaft axis of rotation (152) of the actuator shaft (150).


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    Title :

    ACTUATOR ASSEMBLIES FOR CONTROL SURFACES OF AN AIRCRAFT AND METHOD OF UTILIZING THE SAME


    Additional title:

    AKTUATORANORDNUNGEN FÜR STEUERFLÄCHEN EINES FLUGZEUGS UND VERFAHREN ZUR VERWENDUNG DAVON
    ENSEMBLES ACTIONNEURS POUR DES SURFACES DE COMMANDE D'UN AÉRONEF ET PROCÉDÉ D'UTILISATION DE CEUX-CI


    Contributors:

    Publication date :

    2019-07-10


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge






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