A blade angle feedback ring assembly (200) for an aircraft engine propeller having adjustable angle blades is provided. The feedback ring assembly (200) comprises a feedback ring (204) coupled to rotate with the propeller, the engine configured such that a first electrically-conductive path is defined between the propeller and the engine via the feedback ring (204), and an electric current conduction element provided between the propeller and the engine to define a second electrically-conductive path between the propeller and the engine in parallel to the first path, the second electrically-conductive path configured with a lower electrical resistance to conduction between the propeller and the engine than the first electrically-conductive path.


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    Titel :

    PROPELLER BLADE ANGLE FEEDBACK ARRANGEMENT AND METHOD


    Weitere Titelangaben:

    ANORDNUNG UND VERFAHREN ZUR PROPELLERBLATTWINKELRÜCKMELDUNG
    AGENCEMENT ET PROCÉDÉ DE RÉTROACTION D'ANGLE DE PALE D'HÉLICE


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

    Erscheinungsdatum :

    2024-04-03


    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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