A blade angle feedback assembly for a variable-pitch aircraft propeller rotor rotatable about an axis and having an adjustable blade pitch angle is provided. A feedback device is coupled to rotate with the rotor and to be displaced axially along the axis with adjustment of the blade pitch angle. Sensor(s) mounted adjacent the feedback device are configured to detect a passage of position marker(s) provided on the feedback device as the feedback device rotates. A magnetic shield mounted to the sensor(s) is configured to define a magnetic return path for some magnetic flux of a magnetic field exiting from a first pole of the magnet toward a second pole opposite the first pole. The magnetic shield comprises a wall member positioned adjacent the position marker(s) and configured to span a distance over which the position marker(s) are configured to be displaced with axial displacement of the feedback device.
BLADE ANGLE POSITION FEEDBACK SYSTEM WITH MAGNETIC SHIELD
SYSTEME DE RETROACTION DE POSITION D'ANGLE DE PALE AVEC ECRAN MAGNETIQUE
2021-01-18
Patent
Elektronische Ressource
Englisch
IPC: | G01B MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS , Messen der Länge, der Dicke oder ähnlicher linearer Abmessungen / B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / G01D MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE , Anzeigen oder Aufzeichnen in Verbindung mit Messen allgemein |
BLADE ANGLE POSITION FEEDBACK SYSTEM WITH MAGNETIC SHIELD
Europäisches Patentamt | 2021
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