A blade angle feedback assembly for an aircraft-bladed rotor and an aircraft-bladed rotor system are provided. The rotor is rotatable about a longitudinal axis and has an adjustable blade pitch angle. A feedback device is coupled to rotate with the rotor, the feedback device having a root surface having an edge. At least one position marker extends from the root surface and extends laterally beyond the edge. At least one sensor is mounted adjacent the feedback device and configured to detect a passage of the at least one position marker as the feedback device rotates about the longitudinal axis.
Blade angle position feedback system with extended markers
2020-11-10
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |
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