A blade angle feedback assembly for an aircraft-bladed rotor is provided. The rotor is rotatable about a longitudinal axis and having 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 comprising a non-magnetically permeable body defining a root surface and a plurality of magnetically permeable position markers circumferentially disposed on the root surface, 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 DIFFERING MAGNETIC PERMEABILITY ZONES
APPAREIL DE RETOUR DOTE DE ZONES PERMEABLES MAGNETIQUES DIFFERENTES
2020-11-30
Patent
Electronic Resource
English
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