A blade angle feedback system for an aircraft-bladed rotor rotatable about a longitudinal axis and having an adjustable blade pitch angle is provided. A feedback device is coupled to rotate with the rotor and to move along the axis with adjustment of the blade angle. At least one position marker is affixed to a core of the feedback device and extends along a direction angled relative to the axis. The core is made of a first material having a first magnetic permeability and the position marker comprises a second material having a second magnetic permeability greater than the first magnetic permeability. A sensor is positioned adjacent the feedback device and produces, as the feedback device rotates about the axis, a sensor signal in response to detecting passage of the position marker. A control unit generates a feedback signal indicative of the blade angle in response to the sensor signal.


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    Titel :

    Signal amplification in blade angle position feedback system


    Beteiligte:
    TOMESCU DANA (Autor:in)

    Erscheinungsdatum :

    2023-03-07


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    G01D MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE , Anzeigen oder Aufzeichnen in Verbindung mit Messen allgemein / B64C AEROPLANES , Flugzeuge / G01B MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS , Messen der Länge, der Dicke oder ähnlicher linearer Abmessungen



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