A system and method for providing feedback for an aircraft-bladed rotor (130) about a longitudinal axis (A) and having an adjustable blade pitch angle. At least one position marker (502) is provided at the rotor (130), extends along an axial direction, from a first end (5041) to a second end (5042), and has varying magnetic permeability from the first end (5041) to the second end (504z). At least one sensor (212) is coupled to the rotor (130) and configured for producing, as the rotor (130) rotates about the longitudinal axis (A), at least one sensor signal in response to detecting passage of the at least one position marker (502). A control unit (220) is communicatively coupled to the at least one sensor (212) 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 (212).
PITCH CONTROL ASSEMBLY FOR AN AIRCRAFT-BLADED ROTOR
PITCH-STEUERUNGSANORDNUNG FÜR EINEN FLUGZEUGPROPELLER
ENSEMBLE DE COMMANDE DE PAS POUR UN ROTOR D'AVION À PALES
2024-07-31
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / G01B MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS , Messen der Länge, der Dicke oder ähnlicher linearer Abmessungen / G01D MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE , Anzeigen oder Aufzeichnen in Verbindung mit Messen allgemein / G01P MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION OR SHOCK , Messen der Linear- oder Winkelgeschwindigkeit, der Beschleunigung, der Verzögerung oder des Stoßes |