A blade for an aircraft rotor has a trailing-edge tab, the tab being movable between a stowed position, in which substantially all of the tab is located within the blade, and a deployed position, in which at least a portion of the tab extends from a trailing edge of the blade. At least one actuator system is selectively operable to cause movement of the tab between the stowed position and the deployed position for changing a chord length of the blade.


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    Titel :

    Variable-Chord Rotor Blade



    Erscheinungsdatum :

    11.04.2019


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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