A vibration attenuator is configured for use on an aircraft rotor rotatable about a mast axis and has upper and lower weight assemblies, each comprising a weight with a center of gravity being a radial distance from the mast axis. The weight assemblies are configured for rotation together relative to the rotor at a selected angular rate about the mast axis, the weights being located on opposing sides of the mast axis. A first motor is configured for selective translation of one of the weight assemblies relative to the other weight assembly along the mast axis between a minimum-moment configuration, in which the centers of gravity of the weights revolve about the mast axis in the same plane, and a maximum-moment configuration, in which the centers of gravity of the weights revolve about the mast axis in different planes for producing a whirling moment about the mast axis.


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    Titel :

    VIBRATION ATTENUATOR


    Beteiligte:

    Erscheinungsdatum :

    2022-04-28


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



    VIBRATION ATTENUATOR

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    STAMPS FRANK BRADLEY / HEVERLY DAVID / SMITH MICHAEL R et al. | Europäisches Patentamt | 2022

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    Freier Zugriff

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    STAMPS FRANK BRADLEY / HEVERLY DAVID / SMITH MICHAEL R et al. | Europäisches Patentamt | 2023

    Freier Zugriff

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    HEVERLY DAVID / STAMPS FRANK BRADLEY / CHOI JOUYOUNG JASON et al. | Europäisches Patentamt | 2020

    Freier Zugriff