An electromechanical rudder system control using electromagnetic actuators provides dual redundancy to comply with safety demands. Diversity of possible interconnection distribution allows the manufacturer to choose the proper configuration to satisfy aircraft safety design, hardware savings and overall system quality improvements. A dual channel rudder system architecture includes reconfigurable electronic controllers used to control plural electromechanical primary actuators for rudder control, and a distribution of aircraft and cockpit sensors through the electronic controllers to guarantee minimum required safety standards in case of loss of input data. The plural electromechanical actuators driving a rudder surface are arranged in independent and redundant load paths.


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    Title :

    Rudder system architecture for electrical actuators



    Publication date :

    2024-05-21


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



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