The present disclosure provides methods and systems for controlling a pitch for an aircraft-bladed rotor (130). A plurality of sensor signals are obtained from at least one sensor (212) positioned proximate to a feedback device (300), the feedback device (300) coupled to rotate with the rotor (130) about a longitudinal axis (A) and to move along the longitudinal axis (A) with adjustment of a blade pitch angle of the rotor (130), the sensor signals produced responsive to detecting passage of a plurality of position markers (320) of the feedback device (300), the plurality of position markers (320) spaced circumferentially around the feedback device (300) and having lengths along the longitudinal axis (A) which vary monotonically and incrementally along at least part of the circumference of the feedback device (300). The plurality of sensor signals are processed to identify passage of the plurality of position markers (320). A feedback signal indicative of the blade pitch angle is generated based on the processed sensor signals.


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    Title :

    PITCH CONTROL ASSEMBLY FOR AN AIRCRAFT-BLADED ROTOR


    Additional title:

    BLATTWINKELVERSTELLSTEUERUNGSANORDNUNG FÜR EINEN FLUGZEUGROTOR
    ENSEMBLE DE COMMANDE DE PAS POUR UN ROTOR À PALES D'AÉRONEF


    Contributors:

    Publication date :

    2024-05-22


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

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



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