An aircraft includes a rotor blade and a rotor hub system. The rotor hub system includes a lead-lag damper having a rod end and being operably associated with the rotor blade; a blade adapter having a first arm and an opposing second arm; a pin carried by the blade adapter and configured to secure in position via the first arm and the second arm; and an actuator secured to the pin and configured to adjust the position of the lead-lag rod end relative to the first arm and the second arm.


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    Titel :

    Adjustable Blade-to-Hub Lead-Lag Damper Attachment


    Beteiligte:
    RAUBER RICHARD E (Autor:in) / YUCE MITHAT (Autor:in) / PARHAM JR THOMAS C (Autor:in) / NEWMAN THOMAS J (Autor:in) / WIINIKKA MARK A (Autor:in)

    Erscheinungsdatum :

    2017-09-07


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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