A system is provided for controlling the pitch of blades of a rotor, the system comprising an actuator for each blade, each actuator being configured for selective control of the pitch of an associated blade about a pitch axis. Sensors are configured for determining aerodynamic forces acting on the rotor, and a flight control system is configured to receive signals from the sensors and for operating the actuators in response to the signals to achieve a desired pitch-flap coupling value.


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    Titel :

    Electronic control of blade pitch on a tiltrotor


    Beteiligte:

    Erscheinungsdatum :

    2024-04-09


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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