There is provided a pitch control assembly for a rotor of an aircraft, the rotor rotatable about a longitudinal axis and having blades each rotatable about a span-wise axis to adjust a blade pitch angle thereof, the assembly comprising a plurality of position markers spaced circumferentially around the longitudinal axis and having lengths along the longitudinal axis which vary monotonically and incrementally, at least one sensor configured for producing at least one sensor signal in response to detecting a relative movement between the plurality of position markers and the at least one sensor, and a control unit communicatively coupled to the at least one sensor and configured to generate a feedback signal indicative of the blade pitch angle in response to the at least one sensor signal received from the at least one sensor.
PITCH CONTROL ASSEMBLY FOR AN AIRCRAFT-BLADED ROTOR
2022-03-24
Patent
Elektronische Ressource
Englisch