The invention relates to a vibration isolation device (100) comprising : - a frame (10) intended to be mounted on an engine casing, - an axis (20) intended to be mounted to an external component to isolate, - a resilient member (30) located between said frame (10) and said axis (20), - a fuse mechanism (40) ensuring that said vibration isolation device presents a first stiffness when loads applied to said vibration isolation device (100) are below a predetermined threshold load, and a second stiffness, lower than the first stiffness, when loads applied to the vibration isolation device are at least equal to said predetermined threshold load, wherein said fuse mechanism (40) is arranged, within said vibration isolation device (100), to constrain said resilient member (30) within a predetermined space when the loads applied to the vibration isolation device (100) are below said predetermined threshold load and to release said resilient member so that this latter is capable of deforming beyond said predetermined space when loads applied to the vibration isolation device are at least equal to said predetermined threshold load.


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    Title :

    A VIBRATION ISOLATION DEVICE, ESPECIALLY FOR AIRCRAFT APPLICATIONS


    Additional title:

    UN DISPOSITIF D'ISOLATION DE VIBRATION, SPECIALEMENT DESTINE AUX APPLICATIONS CONCERNANT LES AERONEFS


    Contributors:
    SHAHOSSEINI IMAN (author) / NALL JOHN (author) / ROSON IVAN (author)

    Publication date :

    2018-12-23


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    F16F SPRINGS , Federn / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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