A blade angle feedback assembly (200) for an aircraft-bladed rotor (130) is provided. The rotor is rotatable about a longitudinal axis (A) and has an adjustable blade pitch angle. The assembly comprises a feedback device (204) coupled to rotate with the rotor with adjustment of the blade pitch angle, the feedback device having a root surface (304), a plurality of position markers (208) 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 (206) 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
RÜCKKOPPLUNGSVORRICHTUNG MIT NICHTAXIAL AUSGERICHTETEN POSITIONSMARKERN
DISPOSITIF DE RÉTROACTION COMPORTANT DES MARQUEURS DE POSITION NON AXIALEMENT ALIGNÉS
2023-05-17
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
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