Abstract: Techniques for using a pyrometer to measure one or more operating characteristics of a target are provided. In one example aspect, a pyrometer is oriented relative to a target having target elements spaced from one another such that, as the target is rotated, the pyrometer alternately i) senses a target element for a period of time; and ii) then does not sense any of the target elements for a period of time as no appreciable signal is received. The pyrometer generates an output signal having alternating target pulse widths and null widths. The target and null widths have different amplitudes. The amplitude of the null signal provides an amplitude baseline for which the amplitudes of the target widths or signals may be compared to so that a temperature or other operating characteristic associated with the target can be determined.

Abstract: Systems and methods disclosed herein use a multi-color pyrometer configured to determine a first temperature in a high temperature range and a single-color pyrometer configured to determine second temperature in a low temperature range. The system uses information gained from determination of the first temperature in the high temperature range to facilitate later determining the second temperature in the low temperature range. The first temperature in the high temperature range and the second temperature in the low temperature range are used to monitor and control different engine operations that occur at different times.

Abstract: An apparatus and method for determining a temperature in a system having an object, an optical sensor, and a gas flow passing between the object and the optical sensor, sensing, with the optical sensor, a wavelength emitted from the object and indicative of an attenuation, sensing, with the optical sensor, a wavelength emitted from the object and indicative of a temperature of at least one of the object or the gas; and calculating a temperature of the gas using the wavelengths.

Abstract: An accelerometer includes a controller, a light source operatively coupled to the controller, and a bifurcated waveguide coupled to the light source and configured to receive light output by the light source. The bifurcated waveguide includes a first waveguide portion and a second waveguide portion. The accelerometer also includes a first resonator operatively coupled to the controller and configured to receive light from the first waveguide portion, and a second resonator operatively coupled to the controller and configured to receive light from the second waveguide portion. The first resonator includes a first proof mass, and the second resonator includes a second proof mass.

Abstract: A gas turbine engine and system for measuring torque for a gas turbine engine shaft is provided. The system may include a first sensor module, a second sensor module, a first coupler, a second coupler, and a static antenna. The first and second sensor modules may include strain sensors positioned on the gas turbine engine shaft. The first coupler may be positioned on the gas turbine engine shaft and electrically connected with the first sensor module. The second coupler may be positioned on the gas turbine engine shaft and electrically connected with the second sensor module. The static antenna may include a first band and a second band. The first signal band may be in operable communication with the first sensor module and positioned radially outward from the first coupler. The second signal band may be in operable communication with the second sensor module and positioned radially outward from the second coupler.

Abstract: An accelerometer includes a controller, a light source operatively coupled to the controller, and a bifurcated waveguide coupled to the light source and configured to receive light output by the light source. The bifurcated waveguide includes a first waveguide portion and a second waveguide portion. The accelerometer also includes a first resonator operatively coupled to the controller and configured to receive light from the first waveguide portion, and a second resonator operatively coupled to the controller and configured to receive light from the second waveguide portion. The first resonator includes a first proof mass, and the second resonator includes a second proof mass.

Abstract: An aircraft including a jet engine including a core having a compressor and combustion chamber, and a particulate sensor located within the core and a particulate detection method for an aircraft having a jet engine where the method includes sensing particulates within the core and providing a corresponding value for the sensed particulates and providing an indication related thereto.

Abstract: A gas turbine engine and system for measuring torque for a gas turbine engine shaft is provided. The system may include a first sensor module, a second sensor module, a first coupler, a second coupler, and a static antenna. The first and second sensor modules may include strain sensors positioned on the gas turbine engine shaft. The first coupler may be positioned on the gas turbine engine shaft and electrically connected with the first sensor module. The second coupler may be positioned on the gas turbine engine shaft and electrically connected with the second sensor module. The static antenna may include a first band and a second band. The first signal band may be in operable communication with the first sensor module and positioned radially outward from the first coupler. The second signal band may be in operable communication with the second sensor module and positioned radially outward from the second coupler.

Abstract: A system for measuring torque for a gas turbine engine shaft is provided. The system can include a torque sensor positioned at an engine shaft. The torque sensor, itself, can include a strain sensor for obtaining a strain measurement of the engine shaft and a temperature sensor for obtaining a temperature measurement of the engine shaft. The system can also include a wireless communication element operably connected to the torque sensor for transferring the strain measurement and the temperature measurement. In addition, one or more memory storage units co-located with the torque sensor can be provided. The one or more memory storage units can store calibration information for the system. The calibration information is used by one or more processors to calibrate the strain measurement obtained by the strain and the temperature measurement obtained by the temperature sensor. Methods of using the system are also provided.

Abstract: A strain sensor, a system for monitoring a state of a battery cell, and a battery including the strain sensor. The strain sensor includes a thin, flexible substrate, a plurality of piezoresistors mounted on the substrate, an input for receiving a voltage signal, an output for providing an output voltage signal from the plurality of piezoresistors. The plurality of piezoresistors are connected to form a circuit that is insensitive to a change in temperature and an in-plane deformation of the substrate. The system includes the strain sensor, a source of voltage, and an analysis module configured for receiving a voltage signal based on the output voltage signal provided at the output of the strain sensor and calculating a state of charge or a state of health of a battery cell based on the received voltage signal. The battery includes the strain sensor and a space for spacing adjacent battery cells.

Abstract: The invention is directed to modular flexible sensor arrays that are adaptable, easy to manufacture, and which reduce material waste. A method of making a modular flexible sensor array is provided, including the steps of applying at least one sensing element to a first substrate to form at least one sensor, applying at least one electrically conductive interconnect to a surface of a second flexible substrate, and coupling the at least one sensor to the at least one electrically conductive interconnect such that the at least one sensor is electrically connected thereto.

Abstract: An aircraft including a jet engine including a core having a compressor and combustion chamber, and a particulate sensor located within the core and a particulate detection method for an aircraft having a jet engine where the method includes sensing particulates within the core and providing a corresponding value for the sensed particulates and providing an indication related thereto.

Abstract: A system for sensing the position of a movable object includes a polarization maintaining fiber configured to receive light from a light source; an optical system configured to rotate an angle of polarization of the light by a first predetermined angle; a low birefringence fiber connected to the optical system at a first end and having a mirror connected to a second end configured to reflect the light and rotate the angle of polarization at a second predetermined angle, the second end being configured to overlap a magnetic field of the a magnet attached to the object. The angle of polarization is rotated to a third predetermined angle proportional to at least one of the strength of the magnetic field and an amount of the overlap. The optical system is configured to decompose the third predetermined angle into a first component and a second component. A detector is configured to detect a differential between the first and second components indicative of the amount of the overlap.

Abstract: A battery cell that comprises a sensing platform with sensing elements configured to provide information about in-situ characteristics and parameters of the battery cell. Embodiments of the battery cell can have the sensing platform integrated into the structure of the battery cell, as a separate structure incorporated in the battery cell, and combinations thereof. In one embodiment, the battery cell comprises a sensing platform having sensing elements proximate a localized measurement region, where the sensing platform comprises a substrate with material layers disposed thereon. The material layers comprise at least one sensing layer that forms the sensing elements so that the sensing elements are responsive to properties of the battery cell.

Abstract: A battery cell that comprises a sensing platform with sensing elements configured to provide information about in-situ characteristics and parameters of the battery cell. Embodiments of the battery cell can have the sensing platform integrated into the structure of the battery cell, as a separate structure incorporated in the battery cell, and combinations thereof. In one embodiment, the battery cell comprises a sensing platform having sensing elements proximate a localized measurement region, where the sensing platform comprises a substrate with material layers disposed thereon. The material layers comprise at least one sensing layer that forms the sensing elements so that the sensing elements are responsive to properties of the battery cell.

Abstract: A method of method of forming a wide band-gap semiconductor transient voltage suppressor (TVS) assembly and a system for a transient voltage suppressor (TVS) assembly are provided. The TVS assembly includes a connecting component configured to electrically couple a first electrical component to a second electrical component located remotely from the first electrical component through one or more electrical conduits and a transient voltage suppressor device positioned within the connecting component and electrically coupled to the one or more electrical conduits wherein the TVS device includes a wide band-gap semiconductor material.

Abstract: A system for sensing the position of a movable object includes a polarization maintaining fiber configured to receive light from a light source; an optical system configured to rotate an angle of polarization of the light by a first predetermined angle; a low birefringence fiber connected to the optical system at a first end and having a mirror connected to a second end configured to reflect the light and rotate the angle of polarization at a second predetermined angle, the second end being configured to overlap a magnetic field of the a magnet attached to the object. The angle of polarization is rotated to a third predetermined angle proportional to at least one of the strength of the magnetic field and an amount of the overlap. The optical system is configured to decompose the third predetermined angle into a first component and a second component. A detector is configured to detect a differential between the first and second components indicative of the amount of the overlap.

Abstract: A system for sensing the position of a movable object includes a polarization maintaining fiber configured to receive light from a light source; an optical system configured to rotate an angle of polarization of the light by a first predetermined angle; a low birefringence fiber connected to the optical system at a first end and having a mirror connected to a second end configured to reflect the light and rotate the angle of polarization at a second predetermined angle, the second end being configured to overlap a magnetic field of the a magnet attached to the object. The angle of polarization is rotated to a third predetermined angle proportional to at least one of the strength of the magnetic field and an amount of the overlap. The optical system is configured to decompose the third predetermined angle into a first component and a second component. A detector is configured to detect a differential between the first and second components indicative of the amount of the overlap.

Abstract: A method of method of forming a wide band-gap semiconductor transient voltage suppressor (TVS) assembly and a system for a transient voltage suppressor (TVS) assembly are provided. The TVS assembly includes a connecting component configured to electrically couple a first electrical component to a second electrical component located remotely from the first electrical component through one or more electrical conduits and a transient voltage suppressor device positioned within the connecting component and electrically coupled to the one or more electrical conduits wherein the TVS device includes a wide band-gap semiconductor material.

Abstract: An optical pressure sensor interrogation system is provided. The system includes a light source for providing an optical signal to an optical pressure sensor and an optical coupler for receiving a reflected signal from the optical pressure sensor. The optical coupler splits the reflected signal and provides a first portion of the reflected signal to a first optical detector. The system further includes a filter for receiving a second portion of the reflected signal and providing a filtered signal to a second optical detector and a processing circuitry configured to obtain pressure based on a division or a subtraction of light intensities of the first and the second optical detector output signals. The processing circuitry is further configured to provide a feedback signal to the light source to control a wavelength of the optical signal.