A blade angle feedback assembly for an aircraft-bladed rotor is provided. The rotor is rotatable about a longitudinal axis and has an adjustable blade pitch angle. The assembly comprises a feedback device coupled to rotate with the rotor with adjustment of the blade pitch angle, the feedback device having a root surface, a plurality of position makers circumferentially disposed on the root surface, the plurality of position markers circumferentially spaced from one another and non-aligned with the longitudinal axis, and at least one sensor mounted adjacent the feedback device and configured to detect a passage of the plurality of position markers as the feedback device rotates about the longitudinal axis.
FEEDBACK DEVICE WITH NON-AXIALLY ALIGNED POSITION MARKERS
APPAREIL DE RETOUR DOTE DE MARQUEURS DE POSITION ALIGNES AXIALEMENT
2020-11-30
Patent
Electronic Resource
English
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