A blade angle feedback system (200) for an aircraft-bladed rotor (130) rotatable about a longitudinal axis (A) and having an adjustable blade pitch angle is provided. A feedback device (204) is coupled to rotate with the rotor (130) and to move along the axis (A) with adjustment of the blade angle. At least one position marker (420) is affixed to a core of the feedback device (204) and extends along a direction angled relative to the axis (A). The core is made of a first material (504) having a first magnetic permeability and the position marker (420) comprises a second material (502) having a second magnetic permeability greater than the first magnetic permeability. A sensor (212) is positioned adjacent the feedback device (204) and produces, as the feedback device (204) rotates about the axis (A), a sensor signal in response to detecting passage of the position marker (420). A control unit (220) generates a feedback signal indicative of the blade angle in response to the sensor signal.


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    Title :

    SIGNAL AMPLIFICATION IN BLADE ANGLE POSITION FEEDBACK SYSTEM


    Additional title:

    SIGNALVERSTÄRKUNG IN EINEM SYSTEM ZUR RÜCKMELDUNG DER SCHAUFELWINKELPOSITION
    AMPLIFICATION DE SIGNAUX DANS UN SYSTÈME DE RÉTROACTION DE POSITION D'ANGLE DE PALE


    Contributors:

    Publication date :

    2021-03-10


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    G01P MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION OR SHOCK , Messen der Linear- oder Winkelgeschwindigkeit, der Beschleunigung, der Verzögerung oder des Stoßes / G01D MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE , Anzeigen oder Aufzeichnen in Verbindung mit Messen allgemein / B64C AEROPLANES , Flugzeuge



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