A rotorcraft rotor head has: (i) two or more rotor blades attached to rotate about a rotor axis, and pivot through a flapping and/or teetering hinge, and having a pitch angle; (ii) pitch angle changing means for collectively changing said pitch angle; (iii) centrifugal pitch stop mechanism having an activation point and comprising one or more centrifugal plates; and (iv) control means for providing a control input to said pitch angle changing means; wherein said centrifugal pitch stop mechanism is configured to attain an activated state and to interact with said pitch angle changing means; wherein said activated state is attained when the rotational speed of said rotor blades is greater than said activation point and when a control input is provided by said control means; and wherein said activation point is less than the minimum rotational speed of the rotor blades that is required for flying the rotorcraft.


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    Titel :

    SEMI-AUTOMATIC COLLECTIVE PITCH MECHANISM FOR A ROTORCRAFT


    Weitere Titelangaben:

    HALBAUTOMATISCHER KOLLEKTIVER BLATTVERSTELLUNGSMECHANISMUS FÜR EINEN DREHFLÜGLER
    MÉCANISME SEMI-AUTOMATIQUE DE PAS GÉNÉRAL POUR UN GIRAVION


    Beteiligte:
    FEARN MICHAEL (Autor:in) / FEARN BRIAN (Autor:in)

    Erscheinungsdatum :

    2016-11-09


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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