A blade angle feedback assembly (200) for an aircraft-bladed rotor (130) and an aircraft-bladed rotor system are provided. The rotor (130) is rotatable about a longitudinal axis (A) and has an adjustable blade pitch angle. A feedback device (204) is coupled to rotate with the rotor (130), the feedback device (204) having a root surface (304) having an edge (3021, 3022). At least one position marker (202) extends from the root surface (304) and extends laterally beyond the edge (3021, 3022). At least one sensor (212) is mounted adjacent the feedback device (204) and configured to detect a passage of the at least one position marker (202) as the feedback device (204) rotates about the longitudinal axis (A).
BLADE ANGLE POSITION FEEDBACK SYSTEM WITH EXTENDED MARKERS
SCHAUFELWINKELPOSITIONSRÜCKMELDUNGSSYSTEM MIT ERWEITERTEN MARKERN
SYSTÈME DE RÉTROACTION DE POSITION ANGULAIRE DE PALE AVEC MARQUEURS ÉTENDUS
2022-11-16
Patent
Electronic Resource
English
IPC: | G01D MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE , Anzeigen oder Aufzeichnen in Verbindung mit Messen allgemein / B64C AEROPLANES , Flugzeuge / G01P MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION OR SHOCK , Messen der Linear- oder Winkelgeschwindigkeit, der Beschleunigung, der Verzögerung oder des Stoßes |
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