An aircraft rotor system includes a rotating pitch change shaft which rotates about an axis, a translating element disposed within the rotating pitch change shaft and movable along the axis and a pitch change bearing assembly which transfers movement of the translating element to the pitch change shaft. The pitch change bearing assembly includes a primary bearing and a secondary bearing coupled to the rotating pitch change shaft via the translating element when the primary bearing is in a first mode. A thrust shoulder is coupled to the translating element. The thrust shoulder is movable into engagement with the secondary bearing in response to failure of the primary bearing such that in a second mode, movement of the translating element is primarily transferred to the pitch change shaft via the secondary bearing.


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    Title :

    REDUNDANT HELICOPTER PITCH CHANGE BEARING


    Additional title:

    REDUNDANTES HUBSCHRAUBERSTEIGUNGSWINKELÄNDERUNGSLAGER
    PALIER REDONDANT POUR LE RÉGLAGE DU PAS DE L'HÉLICE D'UN HÉLICOPTÈRE


    Contributors:

    Publication date :

    2022-08-03


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    F16C SHAFTS , Wellen / B64C AEROPLANES , Flugzeuge



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