A blade angle feedback ring assembly for an aircraft engine propeller having adjustable angle blades is provided. The feedback ring assembly comprises a feedback ring 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, 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


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

    Erscheinungsdatum :

    2022-03-22


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / B64C AEROPLANES , Flugzeuge / H01H Elektrische Schalter , ELECTRIC SWITCHES / H02H EMERGENCY PROTECTIVE CIRCUIT ARRANGEMENTS , Schutzschaltungsanordnungen / H05F STATIC ELECTRICITY , Statische Elektrizität



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