A rotor blade pitch actuator has a first and second motor configured to control the rotor blade pitch. An actuator control system is configured to drive the first and second motor such that backlash is either eliminated from the system or minimized to an acceptable level.


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    Titel :

    Anti-Backlash Flight Control Actuator System


    Beteiligte:
    AHYOW BERNARD (Autor:in)

    Erscheinungsdatum :

    27.06.2024


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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