A method of operating a resolver management device according to the present invention includes: generating an excitation signal by using an external control signal; counting a time interval (a first delay time) to a first pole of the excitation signal based on one period of the external control signal by using an internal clock; receiving an excitation signal reflected from a resolver sensor; counting a time interval (a second delay time) to a second pole of the reflected excitation signal at the first pole by using the internal clock; and transmitting a first count value corresponding to the first delay time and a second count value corresponding to the second delay time to a microcontroller unit (MCU).

The present disclosure is directed to a turbine engine (10) defining an axial direction, a radial direction, a circumferential direction, a first end (99) and a second end (98) opposite of the first end (99) along the axial direction. The turbine engine includes a propeller assembly (14) proximate to the first end including a plurality of blades (42) arranged in the circumferential direction disposed around an axial centerline (12), and a feathering mechanism (60) including a hollow piston rod (19). The feathering mechanism rotates the plurality of blades about a pitch axis (13) extended in the radial direction from the axial centerline. The turbine engine further includes a housing (45) proximate to the second end disposed in adjacent arrangement with the propeller assembly in the axial direction. The axial centerline is defined through the propeller assembly and the housing. The turbine engine further includes a beta tube assembly (100) extended through the hollow piston rod and at least partially through the housing in coaxial alignment with the axial centerline. The beta tube assembly defines an at least partially hollow walled pipe (101) extended along the axial direction. The beta tube assembly further defines a plurality of grooves (111, 112) extended along the axial direction proximate to the housing. A first groove (111) extends at least partially in the circumferential direction and along the axial direction to at least partially define a helix (114) corresponding to a rotatable range of the plurality of blades about the pitch axis, and a second groove (112) extends in the axial direction.

The present disclosure is directed to a turbine engine (10) defining an axial direction, a radial direction, a circumferential direction, a first end (99) and a second end (98) opposite of the first end (99) along the axial direction. The turbine engine includes a propeller assembly (14) proximate to the first end including a plurality of blades (42) arranged in the circumferential direction disposed around an axial centerline (12), and a feathering mechanism (60) including a hollow piston rod (19). The feathering mechanism rotates the plurality of blades about a pitch axis (13) extended in the radial direction from the axial centerline. The turbine engine further includes a housing (45) proximate to the second end disposed in adjacent arrangement with the propeller assembly in the axial direction. The axial centerline is defined through the propeller assembly and the housing. The turbine engine further includes a beta tube assembly (100) extended through the hollow piston rod and at least partially through the housing in coaxial alignment with the axial centerline. The beta tube assembly defines an at least partially hollow walled pipe (101) extended along the axial direction. The beta tube assembly further defines a plurality of grooves (111, 112) extended along the axial direction proximate to the housing. A first groove (111) extends at least partially in the circumferential direction and along the axial direction to at least partially define a helix (114) corresponding to a rotatable range of the plurality of blades about the pitch axis, and a second groove (112) extends in the axial direction.

A magnetic field sensor for sensing an absolute position of a target object can include a first one or more magnetic field sensing elements disposed proximate to a first portion of the target object, the first one or more magnetic field sensing elements operable to generate a first magnetic field signal responsive to the movement of the first portion; a second one or more magnetic field sensing elements disposed proximate to a second portion of the target object, the second one or more magnetic field sensing elements operable to generate a second magnetic field signal responsive to the movement of the second portion; a position detection module coupled to use the first and second magnetic field signals to generate a position value indicative of the absolute position; and an output format module coupled to receive the position value and to generate a position signal from the magnetic field sensor indicative of the absolute position.

A magnetic field sensor for sensing an absolute position of a target object can include a first one or more magnetic field sensing elements disposed proximate to a first portion of the target object, the first one or more magnetic field sensing elements operable to generate a first magnetic field signal responsive to the movement of the first portion; a second one or more magnetic field sensing elements disposed proximate to a second portion of the target object, the second one or more magnetic field sensing elements operable to generate a second magnetic field signal responsive to the movement of the second portion; a position detection module coupled to use the first and second magnetic field signals to generate a position value indicative of the absolute position; and an output format module coupled to receive the position value and to generate a position signal from the magnetic field sensor indicative of the absolute position.

An arrangement for cylinder detection in a four-stroke internal combustion engine is disclosed. The arrangement comprises a first disc connected to a crankshaft, the first disc comprising a first mark (M11-M13) within each an interspace angle (), and a second disc connected to a camshaft and comprising one second mark (M21-M26) per number of cylinders. The first mark (M11-M13) is arranged on a first disc, or the plurality of first marks (M11-M13) are arranged in relation to each other on the first disc, and the second marks (M21-M26) are arranged in relation to each other on the second disc such that for each interspace angle () the relevant first mark (M11-M13) is detectable by a first sensor and the relevant second mark (M21-M26) is detectable by a second sensor at different relative rotational positions between the first disc and the second disc.

A system and method for blade angle position feedback. The system comprises an feedback device and a sensor mounted adjacent the feedback device and configured for detecting a passage of position markers on the feedback device during propeller rotation. The position markers are spaced apart from one another around the circumference of the feedback device and are oriented at an angle to one another and to a longitudinal axis. The feedback device and sensor are configured for relative axial displacement. A detection unit is connected to the sensor for receiving the sensor signal therefrom, determining on the basis of the sensor signal a time interval elapsed between the passage of successive position markers, and computing from the time interval blade angle position.

A system and method for blade angle position feedback. The system comprises an feedback device and a sensor mounted adjacent the feedback device and configured for detecting a passage of position markers on the feedback device during propeller rotation. The position markers are spaced apart from one another around the circumference of the feedback device and are oriented at an angle to one another and to a longitudinal axis. The feedback device and sensor are configured for relative axial displacement. A detection unit is connected to the sensor for receiving the sensor signal therefrom, determining on the basis of the sensor signal a time interval elapsed between the passage of successive position markers, and computing from the time interval blade angle position.

A method of operating a resolver management device according to the present invention includes: generating an excitation signal by using an external control signal; counting a time interval (a first delay time) to a first pole of the excitation signal based on one period of the external control signal by using an internal clock; receiving an excitation signal reflected from a resolver sensor; counting a time interval (a second delay time) to a second pole of the reflected excitation signal at the first pole by using the internal clock; and transmitting a first count value corresponding to the first delay time and a second count value corresponding to the second delay time to a microcontroller unit (MCU).

A method of operating a resolver management device according to the present invention includes: generating an excitation signal by using an external control signal; counting a time interval (a first delay time) to a first pole of the excitation signal based on one period of the external control signal by using an internal clock; receiving an excitation signal reflected from a resolver sensor; counting a time interval (a second delay time) to a second pole of the reflected excitation signal at the first pole by using the internal clock; and transmitting a first count value corresponding to the first delay time and a second count value corresponding to the second delay time to a microcontroller unit (MCU).