Actuator for aerospace vehicle comprising an actuating element (4), a motor (1) with a rotor (2), a first rotating element (51), a second rotating element (61), a first and second angle sensor (52, 62) for measuring a first and second angle of the first and second rotating element (51, 61) and an actuator control (7) configured to control the motor (1), based on a current output position of the actuating element (4) and based on the current rotor angle, wherein the current output position of the actuating element (4) and the current angle of the rotor (2) of a current control loop are determined based on the first angle, if the second angle sensor fails, and based on the second angle, if the first angle sensor fails.


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    Title :

    ELECTROMECHANICAL ACTUATOR FAIL OPERATIONAL SENSING SYSTEM BASED ON TWO ANGULAR SENSORS



    Publication date :

    2025-07-03


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    H02K Dynamoelektrische Maschinen , DYNAMO-ELECTRIC MACHINES / B64C AEROPLANES , Flugzeuge



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