A blade angle feedback assembly (200) for an aircraft-bladed rotor (130) is provided. The rotor is rotatable about a longitudinal axis (A) and having an adjustable blade pitch angle. The assembly comprises a feedback device (204) coupled to rotate with the rotor (130) with adjustment of the blade pitch angle, the feedback device (204) comprising a non-magnetically permeable body defining a root surface (304) and a plurality of magnetically permeable position markers (208) circumferentially disposed on the root surface (304), and at least one sensor (206) mounted adjacent the feedback device (204) and configured to detect a passage of the plurality of position markers (208) as the feedback device (204) rotates about the longitudinal axis (A).
FEEDBACK DEVICE WITH DIFFERING MAGNETIC PERMEABILITY ZONES
RÜCKKOPPLUNGSVORRICHTUNG MIT UNTERSCHIEDLICHEN MAGNETISCHEN PERMEABILITÄTSZONEN
DISPOSITIF DE RÉTROACTION AVEC DIFFÉRENTES ZONES DE PERMÉABILITÉ MAGNÉTIQUE
2023-08-02
Patent
Elektronische Ressource
Englisch
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