The present disclosure provides methods and systems for controlling a pitch for an aircraft-bladed rotor. A plurality of sensor signals are obtained from at least one sensor positioned proximate to a feedback device, the feedback device coupled to rotate with the rotor about a longitudinal axis and to move along the longitudinal axis with adjustment of a blade pitch angle of the rotor, the sensor signals produced responsive to detecting passage of a plurality of position markers of the feedback device, the plurality of position markers spaced circumferentially around the feedback device and having lengths along the longitudinal axis which vary monotonically and incrementally along at least part of the circumference of the feedback device. The plurality of sensor signals are processed to identify passage of the plurality of position markers. A feedback signal indicative of the blade pitch angle is generated based on the processed sensor signals.
Pitch control assembly for an aircraft-bladed rotor
2022-03-29
Patent
Electronic Resource
English