A blade angle feedback ring assembly (200) for an aircraft propeller rotatable about a longitudinal axis (A) and having an adjustable blade angle is provided. A feedback ring (204) is coupled to the propeller to rotate therewith and to move along a longitudinal axis (A) with adjustment of the blade angle. A plurality of rods are coupled to the feedback ring (204) and extend along a direction substantially parallel to the longitudinal axis (A), the rods configured to support the feedback ring (204) for longitudinal sliding movement along the longitudinal axis (A) with adjustment of the blade angle. At least one shielding element is provided between the feedback ring (204) and the propeller for shielding the feedback ring (204) from electromagnetism.


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    Title :

    PROPELLER BLADE ANGLE FEEDBACK ARRANGEMENT AND METHOD


    Additional title:

    PROPELLERBLATTWINKELRÜCKMELDUNGSANORDNUNG UND -VERFAHREN
    AGENCEMENT ET PROCÉDÉ DE RÉTROACTION D'ANGLE DE PALE D'HÉLICE


    Contributors:

    Publication date :

    2022-04-13


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

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



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