A blade angle feedback assembly (200) for an aircraft-bladed rotor (130), the rotor (130) rotatable about a longitudinal axis (A) and having an adjustable blade pitch angle, is provided. The assembly (200) comprises a feedback device (204) coupled to rotate with the rotor (130) and to move along the longitudinal axis (A) with adjustment of the blade pitch angle, the feedback device (204) comprising a plurality of position markers (202) circumferentially spaced around the feedback device (204), a plurality of sensors (212, 212A, 212B) positioned adjacent the feedback device (204) and each configured for producing a sensor signal in response to detecting passage of the position markers (202) as the feedback device (204) rotates about the longitudinal axis (A), the sensors (212, 212A, 212B) circumferentially spaced around the feedback device (204) and axially offset along the longitudinal axis (A), and a control unit (220) communicatively coupled to the sensors (212, 212A, 212B) and configured to generate a feedback signal indicative of the blade pitch angle in response to the sensor signals received from the sensors (212, 212A, 212B).


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    Titel :

    BLADE ANGLE POSITION FEEDBACK SYSTEM WITH OFFSET SENSORS


    Weitere Titelangaben:

    BLATTWINKELPOSITIONSRÜCKKOPPLUNGSSYSTEM MIT VERSATZSENSOREN
    SYSTÈME DE RÉTROACTION DE POSITION D'ANGLE DE PALE AVEC CAPTEURS DÉCALÉS


    Beteiligte:
    TOMESCU DANA (Autor:in)

    Erscheinungsdatum :

    2024-01-10


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / G01D MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE , Anzeigen oder Aufzeichnen in Verbindung mit Messen allgemein



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