Abstract: A pylon tracking system for a tiltrotor aircraft includes first and second pylons each having a mechanically redundant pylon conversion actuator with first and second drive systems. A position sensor system includes a first rotary position sensor coupled to the first drive system of the first pylon, a second rotary position sensor coupled to the second drive system of the first pylon, a third rotary position sensor coupled to the first drive system of the second pylon and a fourth rotary position sensor coupled to the second drive system of the second pylon. A flight control computer is configured for cascaded communication with the position sensor system providing at least one excitation voltage to the position sensor system and receiving at least one set of sine and cosine feedback voltages from the position sensor system to identify a differential pylon angle between the first and second pylons during pylon conversion.

Abstract: A pylon tracking system for a tiltrotor aircraft including first and second pylons each having a pylon conversion actuator with primary and backup drive systems. The pylon tracking system includes a plurality of rotary position sensors including a first rotary position sensor coupled to the primary drive system of the first pylon, a second rotary position sensor coupled to the backup drive system of the first pylon, a third rotary position sensor coupled to the primary drive system of the second pylon and a fourth rotary position sensor coupled to the backup drive system of the second pylon. A flight control computer is in communication with the plurality of rotary position sensors and is configured to process feedback therefrom to identify a differential pylon angle between the first and second pylons during pylon conversion operations.

Abstract: A pylon tracking system for a tiltrotor aircraft including first and second pylons each having a pylon conversion actuator with primary and backup drive systems. The pylon tracking system includes a plurality of rotary position sensors including a first rotary position sensor coupled to the primary drive system of the first pylon, a second rotary position sensor coupled to the backup drive system of the first pylon, a third rotary position sensor coupled to the primary drive system of the second pylon and a fourth rotary position sensor coupled to the backup drive system of the second pylon. A flight control computer is in communication with the plurality of rotary position sensors and is configured to process feedback therefrom to identify a differential pylon angle between the first and second pylons during pylon conversion operations.