A system and method for providing feedback for an aircraft-bladed rotor (130) about a longitudinal axis (A) and having an adjustable blade pitch angle. At least one position marker (502) is provided at the rotor (130), extends along an axial direction, from a first end (5041) to a second end (5042), and has varying magnetic permeability from the first end (5041) to the second end (504z). At least one sensor (212) is coupled to the rotor (130) and configured for producing, as the rotor (130) rotates about the longitudinal axis (A), at least one sensor signal in response to detecting passage of the at least one position marker (502). A control unit (220) is communicatively coupled to the at least one sensor (212) and configured to generate a feedback signal indicative of the blade pitch angle in response to the at least one sensor signal received from the at least one sensor (212).


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    Title :

    BLADE ANGLE FEEDBACK DEVICE WITH VARIABLE MAGNETIC PERMEABILITY


    Additional title:

    VORRICHTUNG ZUR ERFASSUNG DES BLATTANSTELLWINKELS MIT VARIABLER MAGNETISCHER PERMEABILITÄT
    DISPOSITIF DE DÉTECTION DE L'ANGLE D'INCLINAISON DES PALES À PERMÉABILITÉ MAGNÉTIQUE VARIABLE


    Contributors:

    Publication date :

    2023-10-11


    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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