A rotorcraft vibration isolation system includes a plurality of liquid inertia vibration elimination (LIVE) units mounted on a first rotorcraft surface, an accumulator mounted on a second rotorcraft surface at a location that is remote from locations of the plurality of LIVE units, and a fluid passage to connect the accumulator to the plurality of LIVE units in parallel. The fluid passage has sufficient length to traverse between the location of the accumulator and each location of each LIVE unit. During rotorcraft operation, the second rotorcraft surface experiences lesser periodic vibration than the first rotorcraft surface.


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    Titel :

    ROTORCRAFT VIBRATION ISOLATION SYSTEMS


    Beteiligte:
    SMITH MICHAEL (Autor:in) / STAMPS FRANK BRADLEY (Autor:in) / LEE TAEOH (Autor:in) / HEVERLY II DAVID E (Autor:in)

    Erscheinungsdatum :

    2015-10-29


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F16F SPRINGS , Federn / B64C AEROPLANES , Flugzeuge



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