A target configured to be used with a position sensor for sensing a position of the target is described. The target includes at least one elongated conductive loop structure for allowing eddy currents to flow therein and configured to affect a magnetic field received from the position sensor in a preferred direction along the at least one elongated conductive loop structure.

A displacement transducer for a valve in a housing includes a cylindrical displacement transducer core, a coil, a coil housing, and a compensation element. The coil is positioned in the coil housing, and radially encloses the core. The coil housing has a first side supported by the housing, and a supporting face positioned between the first side and an axial end side of the coil housing facing away from the valve such that a length change of the coil is not limited in an axial direction facing away from the valve. The housing is axially supported on the compensation element via the supporting face. A side of the compensation element facing away from the valve is supported on one or more of (i) an adjustable cover, (ii) a standard component of a supporting chain of the core, and (iii) a component formed from a material with a suitable coefficient of thermal expansion.

An apparatus for sensing a rotating body includes a unit to be detected including a first pattern portion having first patterns and a second pattern portion having second patterns, and configured to rotate around a shaft, a sensor module including a first sensor and a third sensor disposed opposite to the first pattern portion with the rotating shaft interposed therebetween, a second sensor and a fourth sensor disposed opposite to the second pattern portion with the rotating shaft interposed therebetween, and a rotation information calculator configured to calculate a first compensation sensing value based on a sum of a sensing value of the first sensor and a sensing value of the third sensor, and to calculate a second compensation sensing value based on a sum of a sensing value of the second sensor and a sensing value of the fourth sensor.

A position sensing system for measuring a position of a moving object includes an electromagnet configured to generate an alternating magnetic field, and a magnetic sensor configured to measure an intensity of a first magnetic field that is based on the alternating magnetic field. A controller is configured to estimate a position of the moving object based on the measured intensity of the first magnetic field.

A blade angle feedback system for an aircraft-bladed rotor rotatable about a longitudinal axis and having an adjustable blade pitch angle is provided. A feedback device is coupled to rotate with the rotor and to move along the axis with adjustment of the blade angle. At least one position marker is affixed to a core of the feedback device and extends along a direction angled relative to the axis. The core is made of a first material having a first magnetic permeability and the position marker comprises a second material having a second magnetic permeability greater than the first magnetic permeability. A sensor is positioned adjacent the feedback device and produces, as the feedback device rotates about the axis, a sensor signal in response to detecting passage of the position marker. A control unit generates a feedback signal indicative of the blade angle in response to the sensor signal.

There is provided a blade angle feedback system for an aircraft-bladed rotor rotatable about a longitudinal axis and having an adjustable blade pitch angle. A feedback device is coupled to rotate with the rotor and to move along the axis with adjustment of the blade pitch angle. The feedback device comprises a body having position marker(s) embedded therein, the body made of a first material having a first magnetic permeability and the position marker(s) comprising a second material having a second magnetic permeability greater than the first. Sensor(s) are positioned adjacent the feedback device and configured for producing, as the feedback device rotates about the axis, sensor signal(s) in response to detecting passage of the position marker(s). A control unit is communicatively coupled to the sensor(s) and configured to generate a feedback signal indicative of the blade pitch angle in response to the sensor signal(s) received from the sensor(s).

A system and method for providing feedback for an aircraft-bladed rotor about a longitudinal axis and having an adjustable blade pitch angle. At least one position marker is provided at the rotor, extends along an axial direction, from a first end to a second end, and has varying magnetic permeability from the first end to the second end. At least one sensor is coupled to the rotor and configured for producing, as the rotor rotates about the longitudinal axis, at least one sensor signal in response to detecting passage of the at least one position marker. A control unit is 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.

A feedback device for use in a gas turbine engine, and methods and systems for controlling a pitch for an aircraft-bladed rotor, are provided. The feedback device is composed of a circular disk and a plurality of position markers. The circular disk is coupled to rotate with a rotor of the gas turbine engine, to move along a longitudinal axis of the rotor, and has first and second opposing faces defining a root surface that extends between and circumscribes the first and second faces. The plurality of position markers extend radially from the root surface and are circumferentially spaced around the circular disk. The position markers have a top surface elevated with respect to the root surface and opposing first and second side surfaces. The side surfaces of the position markers have a curved concave profile extending toward the root surface.

A feedback device for use in a gas turbine engine, and methods and systems for controlling a pitch for an aircraft-bladed rotor, are provided. The feedback device is composed of a circular disk and a plurality of position markers. The circular disk is coupled to rotate with a rotor of the gas turbine engine, to move along a longitudinal axis of the rotor, and has first and second opposing faces defining a root surface that extends between and circumscribes the first and second faces. The plurality of position markers extend radially from the root surface, are circumferentially spaced around the circular disk, and extending along the longitudinal axis from a first end portion to a second end portion. At least part of the first end portion and/or of the second end portion comprises a material having higher magnetic permeability than that of a remainder of the position markers.

In one embodiment, a position sensor assembly is disclosed. The position sensor assembly includes a first bearing ring defining a first bearing raceway, and a second bearing ring defining a second bearing raceway. A ferromagnetic component is arranged on the first bearing ring. The ferromagnetic component defines a surface that has a non-uniform circumferential profile that varies for at least 90 degrees in a circumferential direction. An inductor assembly is arranged on the second bearing ring, and the inductor assembly includes at least two inductors that are circumferentially spaced from each other by at least 90 degrees.