There is provided a blade angle feedback assembly for a propeller of an aircraft engine. The propeller is rotatable about an axis and has propeller blades rotatable about respective spanwise axes to adjust a blade angle thereof. The blade angle feedback assembly comprises a feedback ring having a plurality of position markers disposed thereon, at least one sensor configured to provide feedback on the blade angle of the propeller blades by detecting a relative movement between the feedback ring and the at least one sensor, and at least one shielding element provided between the feedback ring and the propeller, the at least one shielding element configured to shield the feedback ring from electromagnetism.


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    Titel :

    Propeller blade angle feedback arrangement and method


    Beteiligte:
    MARONE JOSEPH ERNESTO (Autor:in) / YAKOBOV ELLA (Autor:in) / FARRELL IAN (Autor:in) / BASSE OLIVIER (Autor:in) / DOBSON MARTIN (Autor:in) / CLERMONT MARTIN (Autor:in) / LAVOIE MARC (Autor:in)

    Erscheinungsdatum :

    2023-10-10


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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