1694results about "Gyroscopes/turn-sensitive devices" patented technology

The invention discloses a hemispherical harmonic oscillator high-precision equal-mass-density modification method, which comprises the following steps: determining the axis direction of a central anchor post of a hemispherical harmonic oscillator through multi-position detection analysis, and taking the axis direction as a measurement basis; measuring three-dimensional contour point cloud coordinates of the outer spherical surface and the inner spherical surface and eccentric coordinates relative to the axis reference, and establishing actual contour models of the outer spherical surface and the inner spherical surface; a modification area and a corresponding removal thickness are determined, and a three-dimensional modification removal model is established; carrying out three-dimensional continuous modification removal processing on the to-be-modified areas of the outer spherical surface and the inner spherical surface by adopting an etching method; and evaluating a modification result according to the middle surface diameter and thickness distribution of the section circles of the outer spherical surface and the inner spherical surface. According to the invention, the mass trimming of the three-dimensional spherical shell of the hemispherical resonator can be realized, and the hemispherical resonator with relatively symmetrical mass density distribution can be obtained through the combined mass trimming of the outer spherical surface and the inner spherical surface, so that the precision of the hemispherical resonator gyroscope can be improved.

The present invention discloses a mold and method for thermoforming a micro-hemispherical resonator based on full mold constraint. The mold comprises a main body and a forming ball. The main body has a cavity recessed downward from its top surface, the cavity having a plurality of air holes communicating with the exterior of the main body, and the bottom of the cavity has positioning holes. The forming ball is placed in the cavity through the positioning holes. The shape parameters of the forming ball match the shape parameters of the inner cavity of the micro-hemispherical resonator. The method for thermoforming a micro-hemispherical resonator employs the above-mentioned mold to form the micro-hemispherical resonator. Compared with the prior art, the present invention utilizes a precisely machined forming ball to constrain the shape of the micro-hemispherical resonator during the forming process, thereby further improving the structural symmetry of the micro-hemispherical resonator and enabling control of the shape parameters of the micro-hemispherical resonator.

The invention discloses a percussion drill anti-deviation intelligent correction system and method based on gyroscopes, and particularly relates to the technical field of intelligent correction.The method includes the steps that motion data of a percussion drill are collected through the multiple gyroscopes, the motion data are preprocessed and compared with a preset path, and the collection error of each gyroscope is calculated; then, the percussion drill is partitioned, and the temperature and the vibration state of each region are monitored; according to the temperature and vibration conditions, each area is endowed with a weight, and a comprehensive error is obtained through a weighted average method. Then, actual errors (such as position, angle and speed errors) are converted into fuzzy values, and a fuzzy set is defined to represent the errors and the change rate of the errors; through fuzzification processing, input errors are mapped to corresponding fuzzy sets. And deducing control output by using a fuzzy inference engine. And finally, a reasoning result is converted into a clear control signal, and the system performs control or correction according to the signal to ensure accurate adjustment.

The invention discloses a hemispherical resonator gyroscope inertial navigation system temperature compensation method and compensation system, and the method comprises the steps: constructing a dynamic temperature space model, and achieving temperature drift characteristic modeling; designing an incremental adaptive neural network structure to enable the compensation model to adapt to the temperature change, and optimizing the compensation precision through a successive approximation incremental learning mode; temperature compensation and increment optimization are carried out in real time through combination of a dynamic temperature space model and an increment adaptive neural network, and compensation precision is maintained through dynamic updating of a temperature space and an increment learning mechanism of the increment adaptive neural network; output signal drift and compensation errors are monitored through a self-adaptive feedback mechanism, a dynamic temperature space model and incremental self-adaptive neural network parameters are dynamically adjusted, and the stability and the compensation effect are improved through an online correction and model self-optimization mechanism. According to the method, the problems of insufficient temperature drift modeling precision, poor adaptability and compensation precision attenuation after long-time operation in a traditional compensation method are solved.

The invention discloses a hemispherical gyroscope phase-locking control optimization method and device, and the method comprises the steps: changing the vibration mode azimuth angles of a hemispherical resonator gyroscope, collecting the phase-locking frequency in real time for each vibration mode azimuth angle, and calculating the phase-locking optimization control force in real time according to the collection result, substituting the phase locking frequency and the phase locking optimization control force into an electrode driving excitation model to calculate a driving signal in real time and transmit the driving signal to a driving electrode, and after the phase locking frequency is stable, collecting a stable phase locking optimization control force corresponding to the vibration mode azimuth angle; according to all the vibration mode azimuth angles and the corresponding stable phase-locking optimization control force, constructing a relation model of the two, solving the relation model to obtain phase-locking optimization parameters, calculating the phase-locking optimization control force according to the phase-locking optimization parameters and the relation model, and substituting the phase-locking optimization control force into an electrode driving excitation model to calculate a driving signal. Therefore, the compensation for the driving signal when the hemispherical resonator gyroscope works normally is realized. According to the invention, the influence of the circumferential frequency difference on the output precision of the harmonic oscillator can be eliminated.

The invention discloses a hemisphere gyroscope driving crosstalk rapid self-identification and compensation method and device, and the method comprises the steps: carrying out four rounds of experiments according to a resonant frequency and a preset amplitude range, gradually increasing the amplitude in the preset amplitude range in each round, and for each amplitude, carrying out the self-identification and compensation of the driving crosstalk of a hemisphere gyroscope. A driving signal is calculated in real time within a set time range and transmitted to a driving electrode, and a detection signal of a detection electrode is collected at the same time; the method comprises the following steps: acquiring a detection signal simplification model, decomposing the detection signal according to the detection signal simplification model, constructing a crosstalk parameter identification model according to all driving signals and corresponding detection signals, solving the parameter identification model, and substituting crosstalk identification parameters into a crosstalk compensation model so as to realize crosstalk compensation of the detection signal when the hemispherical resonator gyroscope works normally. According to the method, the accuracy of driving crosstalk compensation of the hemispherical gyroscope can be effectively improved, so that the control precision and the zero-bias stability of the gyroscope are improved.

The present disclosure relates to a MEMS inertial sensor device in a semiconductor chip package that includes an integrated circuit configured to process inertial sensor data. Preferred implementations utilize inertial sensors having different sensitivity ranges to adjust operation of dynamic system control such as motion and or attitude control of autonomous vehicles.

The invention relates to the technical field of gyroscopes, and discloses a hemispherical resonator gyroscope scale error compensation method, device and equipment and a medium. The method comprises the following steps: acquiring a target temperature value, and acquiring a target resonant frequency value according to the target temperature value; according to the target resonant frequency value and a pre-calibrated temperature compensation coefficient, calculating to obtain a target electrode asymmetric error coefficient; according to the asymmetric error coefficient of the target electrode, a target gyroscope scale factor is obtained through calculation, and according to the target gyroscope scale factor, the output angular velocity of the target gyroscope is obtained through calculation. According to the scheme of the embodiment, the asymmetric error of the gyroscope electrode is subjected to temperature compensation correction, so that the scale error of the hemispherical resonator gyroscope can be reduced, and the precision of the gyroscope can be improved.

The invention relates to the technical field of hemispherical resonator gyroscopes, in particular to a method for reducing vibration coupling of a hemispherical resonator gyroscope, and aims to solve the problem that accurate vibration suppression is often difficult to realize when the HRG faces a complex and multi-frequency mixed vibration environment. Comprising the following steps: step 1, evaluating the frequency range, amplitude and directivity of an external vibration environment; 2, a vibration isolation module is installed to reduce transmission of external vibration; 2, analyzing external vibration characteristics of the hemispherical resonator gyroscope; 3, generating a compensation signal based on the vibration characteristics of the hemispherical resonator gyroscope, and compensating the vibration signal of the hemispherical resonator gyroscope in real time through a compensation system; and 4, debugging and optimizing a vibration isolation and compensation system. By adopting a vibration isolation and active compensation method, external vibration and internal structure coupling vibration are controlled, the interference of vibration coupling on the hemispherical resonator gyroscope is reduced, the performance of the hemispherical resonator gyroscope is improved, and the use requirements in high-precision navigation and complex environments are met.

The invention provides a hemispherical resonator gyroscope which comprises a hemispherical resonator, a driving electric substrate and a detection electric substrate, the hemispherical resonator is of a hemispherical structure, the driving electric substrate is of a flat plate type structure, and the detection electric substrate is of an inner spherical surface structure. A first conductive film layer is arranged on the inner surface of the hemispherical harmonic oscillator, a second conductive film layer is arranged on the end face of the lip edge, the detection electric substrate is provided with a detection electrode, and the driving electric substrate is provided with a potential electrode and a driving electrode. The detection electrode and the first conductive film layer form a detection capacitor, and the driving electrode and the second conductive film layer form a driving capacitor. The detection electrode and the driving electrode are separately arranged, so that the coupling of the driving signal and the detection signal can be reduced. The detection electric substrate is of an inner spherical surface structure, so that the area of a detection capacitor formed by the detection electrode and the first conductive film layer can be increased, and the intensity of a detection signal is improved. The driving electric substrate is of a flat plate type structure, and the potential electrode and the driving electrode are arranged on the driving electric substrate, so that the processing and assembling difficulty can be reduced.

The invention relates to a rapid detection method for the resonant frequency of a hemispherical harmonic oscillator, belongs to the technical field of inertial measurement, solves the problems of long measurement time and low detection precision in the measurement of the second-order resonant frequency of the hemispherical harmonic oscillator in the prior art, and comprises the following steps: S1, providing a voltage excitation source, and applying a broadband sinc excitation signal to the hemispherical harmonic oscillator; s2, continuously recording the detection data in a set continuous recording time period; s3, performing frequency mixing to obtain data after frequency mixing; step S4, carrying out anti-aliasing filtering and down-sampling on the data after frequency mixing; step S5, carrying out N-point fast Fourier transform on the downsampled data to obtain a frequency spectrum of the detection signal; s6, based on the frequency spectrum of the converted detection signal, determining the frequency corresponding to the peak value of the frequency spectrum, and obtaining the measured second-order resonant frequency of the hemispherical harmonic oscillator; and S7, based on the measured second-order resonant frequency of the hemispherical harmonic oscillator, performing frequency phase loop, amplitude loop closed loop and orthogonal closed loop on the hemispherical harmonic oscillator.

The invention relates to the technical field of hemispherical harmonic oscillator assembly, in particular to a welding method and device for an assembled hemispherical harmonic oscillator, and the device comprises a vibration welding platform and a clamping assembly located above the vibration welding platform; the vibration welding platform is used for bearing the sensitive base and providing a thermal field and a vibration field needed by welding, and the clamping assembly is used for clamping the center shaft and sending the center shaft into a center hole of the base. A heating unit and a composite vibration ultrasonic transducer are arranged in the platform, and the platform is configured to apply high-frequency vibration formed by superposition of vertical longitudinal waves and horizontal torsional waves to the base. The high-frequency vibration thixotropic effect is used for reducing the viscosity of the molten solder, the ultrasonic cavitation effect is used for forcibly discharging bubbles at the bottom of the blind hole, and the sound radiation pressure generated by the vibration standing wave field is used for driving the center shaft to achieve friction-free self-centering in the hole. According to the device, the problems of air bolt pseudo soldering and rigid assembly clamping stagnation in the traditional process are solved, and the assembly coaxiality and the connection strength of the harmonic oscillator are remarkably improved.

The invention relates to an automatic test method and system for the zero offset of a hemispherical resonator gyroscope. The automatic test system composed of a double-shaft servo turntable control module, a gyroscope control module and a PC (Personal Computer) upper computer is built; a servo turntable control instruction and a gyroscope control instruction are sent through a serial port according to a certain program through an automatic test logic built in a PC upper computer, a gyroscope vibration mode angle is controlled to be automatically switched from 0 degree to 360 degrees (the step length can be set), and turntable angle and gyroscope vibration mode angle data under each vibration mode angle are synchronously collected; and substituting the acquired data into the error model, completing zero offset error parameter identification by adopting a nonlinear least square method, generating an error compensation formula, and writing the error compensation formula into a gyroscope control unit in real time to realize compensation.

Exemplary system, method and computer-accessible medium for selecting at least one location of (i) at least one receiver or transceiver or (ii) at least one transmitter or transceiver can be provided. For example, it is possible to facilitate a receipt, from the at least one transmitter or transceiver, of a plurality of signals by the receiver(s) or transceiver(s). Each of the signals has a multipath component. Then, it is possible to determine time of flight (ToF) information and angle of arrival (AoA) information of the multipath components present in the signals. Further, it is possible to determine one or more possible locations of (i) the receiver(s) or transceiver(s) or (ii) the transmitter(s) or transceiver(s) based on the ToF information, the AoA information, and a model of physical surroundings. The location(s) of (i) the receiver(s) or transceiver(s), or (ii) the transmitter(s) or transceiver(s) can be selected based on the one or more possible locations and an extended Kalman filter (“EKF”).

A yaw rate sensor and a method for operating a yaw rate sensor comprising a substrate and a double rotor are proposed, wherein the substrate has a main extension plane with an X direction and a Y direction running perpendicular thereto, wherein the double rotor has a first rotor and a second rotor which - spaced apart along the X direction and separated from one another by a central region - are elastically connected to the substrate via a respective suspension and which are elastically connected to one another via a first coupling element such that the two rotors can be excited to antiphase torsional oscillations, wherein the rotation axes of the rotors run in a Z direction perpendicular to the main extension plane of the substrate, wherein the yaw rate sensor has first detection electrodes and second detection electrodes, wherein the first rotor is connected to a first seismic mass and a second seismic mass such thatthat these are each mounted so as to be deflectable in the radial direction relative to the first rotor and substantially parallel to the main extension plane, wherein the second rotor is connected to a third seismic mass and a fourth seismic mass in such a way that these are each mounted so as to be deflectable in the radial direction relative to the second rotor and substantially parallel to the main extension plane, wherein the first seismic mass is connected to the third seismic mass via a first rocker element in such a way that the third seismic mass is deflected in a direction opposite to the radial deflection of the first seismic mass upon a radial deflection of the first seismic mass, wherein the second seismic mass is connected to the fourth seismic mass via a second rocker element in such a way that the fourth seismic mass is deflected in a direction opposite to the radial deflection of the first seismic mass upon a radial deflection of the second seismic mass,the radial deflection of the second seismic mass is deflected in the opposite direction, wherein the first and second rocker elements are elastically connected to one another via a second coupling element such that the radial deflections of the first and second seismic masses are antiparallel and the radial deflections of the third and fourth seismic masses are also antiparallel.

The invention provides a cattle behavior recognition method based on a three-axis attitude angle, and belongs to the technical field of intelligent animal husbandry management. According to the method, three-axis attitude angle signals such as the yaw angle (Yaw), the pitch angle (Pitch) and the roll angle (Roll) of the head of a cattle are collected in real time through a gyroscope sensor arranged in wearable equipment such as a cattle ear tag. The method does not depend on images, accelerometers, microphones or other modalities, only based on attitude angle signals, multiple algorithms such as a time sequence sliding window, frequency domain analysis, weighted scoring, sudden change detection and state transition modeling are utilized, and multiple typical behaviors such as ingestion, rumination, water drinking, bed lying, limping, licking, fright jumping and low activity are recognized. The method is suitable for multiple cattle breeds such as dairy cattle, beef cattle and buffalo, has the advantages of low power consumption, lightweight calculation, low deployment cost, accurate identification and the like, and is convenient for realizing behavior monitoring and health management of large-scale cattle individuals. The algorithm path can be flexibly selected, but a core input signal is only limited to attitude angle data, so that the technical boundary of the patent protection of the method is formed.

An inertial measurement device includes: an inertial sensor; a first signal processing circuit; a second signal processing circuit; a first communication unit and a second communication unit configured to communicate with an external device; and a mode selection unit configured to select a processing mode from a plurality of modes including a first processing mode and a second processing mode. The first processing mode is a mode in which the inertial measurement device is used alone and outputs a signal processed by the first signal processing circuit from the first communication unit, and the second processing mode is a mode in which the inertial measurement device is used in a state of being coupled to another inertial measurement device, a first signal processed by the first signal processing circuit and a second signal from another inertial measurement device received from the second communication unit are subjected to a calculation process by the second signal processing circuit, and a signal subjected to the calculation process is output from the first communication unit.

The invention relates to the technical field of angular velocity measurement, and discloses a drilling tool rotating body angular velocity measurement method, system and device and a storage medium, and the method comprises the steps: generating a compensation database of the incidence relation between temperature gradient data and angular velocity deviation data; an asymmetric elastic supporting structure is installed, and energy dissipation parameters are generated; establishing an association rule of the temperature gradient data and the energy dissipation parameters, and generating a dynamic compensation rule under the combined action of temperature and vibration; decomposing the angular velocity deviation data according to a dynamic compensation rule to generate a dynamic compensation amount, and adjusting weight distribution of temperature and vibration intensity in the dynamic compensation amount through an acquired accelerometer feedback signal; and continuously injecting the adjusted dynamic compensation amount into a drift correction loop to enable the corrected gyroscope output signal and the accelerometer feedback signal to form closed-loop control, and maintaining stable output of the angular velocity measurement value of the rotary body through autonomous iterative optimization of a dynamic compensation rule. According to the invention, the angular velocity measurement precision and stability can be improved.

The invention provides an MEMS gyroscope and electronic equipment. The MEMS gyroscope comprises a center anchor point, a driving unit, driving pieces and an electrode assembly, wherein the driving pieces are symmetrically arranged on the left side and the right side of the center anchor point relative to the center anchor point, and the electrode assembly provides driving force for a gyroscope structure; the mass block unit comprises first detection mass blocks, second detection mass blocks, third detection mass blocks and decoupling units, the first detection mass blocks are symmetrical about the center anchor point and arranged on the outer side of the driving part, the second detection mass blocks are arranged on the upper side and the lower side of the center anchor point respectively, and the third detection mass blocks are arranged on the inner side of the driving part respectively. Comprising a decoupling mass block arranged between the center anchor point and the third detection mass block, one side of the decoupling mass block is connected to the center anchor point through a first coupling beam, and the other side of the decoupling mass block is connected to a first anchor point of a base through a first guide beam. According to the invention, Z-axis driving and detection decoupling can be realized, the coupling error is reduced, and the gyroscope detection precision is improved.

The invention relates to an all-angle hemispherical gyroscope delay and damping asymmetric error joint compensation method, which belongs to the technical field of inertial navigation, and comprises the following steps: S1, obtaining a self-precession excitation signal and an angular velocity measurement value signal output by a gyroscope; s2, preliminarily estimating the time delay of the gyroscope by adopting a maximum likelihood weighted cross-correlation time delay estimation method; s3, estimating the damping asymmetry error of the gyroscope through a recursive least square method by utilizing the estimated time delay; s4, re-estimating the time delay of the gyroscope by using the estimated damping asymmetric error to obtain the updated estimated time delay; judging whether the updated estimated delay is converged or not; if not, returning to the step S3, and re-estimating the damping asymmetric error of the gyroscope through the recursive least square method by utilizing the updated estimated delay; if the time delay is converged, the finally estimated time delay is obtained; and S5, compensating the finally estimated delay and damping asymmetric error into a control system of the gyroscope. According to the invention, the measurement precision and long-term stability of the gyroscope are improved.

The invention discloses a simulation verification method for an ASIC (Application Specific Integrated Circuit) control loop of a metal micro-resonance hemisphere-like gyroscope. The method comprises the following steps: based on an input angular velocity and a control signal, generating a vibration signal of a harmonic oscillator by using a pre-constructed dynamics simulation model; modulating and demodulating the vibration signal through a signal modulation and demodulation module, extracting a low-frequency component and removing high-frequency noise to obtain a parameter representing a modal precession state; an antinode control signal and a wave node control signal are generated through a PID controller module based on the parameters representing the modal precession state; an antinode control signal and a wave node control signal are decomposed to an orthogonal direction through a coordinate transformation and combination module to generate a driving signal, and the driving signal is applied to a harmonic oscillator to form a closed-loop self-excitation driving control loop; and verifying the dynamic performance of the closed-loop self-excitation driving control loop in a simulation environment. The technical problems of high power consumption, complexity and development cost of simulation verification are solved.

The present invention discloses a method and system for online calibration of the control loop phase error of a hemispherical resonant gyroscope. The method comprises the following steps: constructing a drive modal transfer function for the hemispherical resonant gyroscope and plotting an amplitude-frequency characteristic curve and a phase-frequency characteristic curve based on the drive modal transfer function; performing frequency domain analysis on the drive modal transfer function of the hemispherical resonant gyroscope based on the amplitude-frequency characteristic curve and the phase-frequency characteristic curve to obtain analysis results; and online calibrating phase error parameters based on the analysis results to compensate for the control loop phase error. The method is simple to operate and requires no external instrumentation. The hemispherical resonant gyroscope only requires normal operation; the remaining calculations are performed by a program. Furthermore, the method is adaptable, as component inconsistencies do not affect the testing process. Therefore, the method is suitable for measuring the phase errors of drive and detection signals in closed-loop control gyroscopes.

A method for iteratively compensating for detection, drive, and phase errors in a dual-channel measurement and control system for a hemispherical resonant gyroscope belongs to the field of inertial technology. The present invention solves the problem that detection channel errors, drive channel errors, and signal phase delay errors can cause undesirable drift in the standing wave angular rate output by the gyroscope. The present invention effectively suppresses individual errors by performing iterative compensation through a compensation matrix, effectively reduces coupling interference between errors through the design of a compensation scheme, and ultimately achieves optimal compensation for the three errors. By iteratively compensating for detection, drive, and phase errors, the signal detection accuracy and excitation application accuracy of the rate-integrating hemispherical resonant gyroscope dual-channel measurement and control system are improved, effectively solving the problem of undesirable drift in the standing wave angular rate caused by gain, deflection error, and phase delay error generated in the detection channel and drive channel of the measurement and control system. The method of the present invention can be applied to error compensation in a dual-channel measurement and control system for a hemispherical resonant gyroscope.

The invention discloses a hemispherical resonator gyroscope two-channel measurement and control system detection, driving and phase error iterative compensation method, and belongs to the technical field of inertia. According to the invention, the problem of unexpected drift of the standing wave angular rate output by the gyroscope due to detection channel errors, driving channel errors and signal phase delay errors is solved. According to the method, iterative compensation is carried out through the compensation matrix to achieve effective suppression of a single error, coupling interference between errors is effectively reduced through compensation scheme design, and finally the optimal compensation effect on the three errors is achieved. Through iterative compensation of detection, driving and phase errors, the signal detection precision and excitation application precision of the double-channel measurement and control system of the rate integration hemispherical resonator gyroscope are improved, and the problem of unexpected drift of the standing wave angular rate caused by gain and drift angle errors and phase delay errors generated by a detection channel and a driving channel of the measurement and control system is effectively solved. The method provided by the invention can be applied to error compensation of a hemispherical resonator gyroscope double-channel measurement and control system.

A gyroscope structure, a chip, a gyroscope and an electronic device, the gyroscope structure comprises a substrate and a structural layer, the structural layer comprises an anchor point, a first elastic structure, a second elastic structure, a third elastic structure, a lever, a first mass block and a second mass block, the anchor point is connected with the substrate, the third elastic structure is used for connecting the anchor point with the lever, and the second elastic structure is used for connecting the first mass block and the second mass block. The first elastic structure is used for connecting the lever with the first mass block, and the second elastic structure is used for connecting the lever with the second mass block. Therefore, the orthogonality problem caused by micromachining manufacturing can be inhibited and counteracted through torsion of the first lever, and the precision and the stability of the gyroscope are improved.

The invention discloses a method for detecting the wind resistance of a rotor unmanned aerial vehicle, relates to the technical field of unmanned aerial vehicle detection, and mainly aims to provide a method capable of accurately positioning the position of the unmanned aerial vehicle and judging and detecting changes of a flight pitch angle, a rolling angle and a deflection angle of the unmanned aerial vehicle. According to the main technical scheme, the method for detecting the wind resistance of the unmanned rotorcraft comprises the steps that a reference point is fixed on the ground, and a space rectangular coordinate system is established; starting a laser tracking device to align the detected unmanned aerial vehicle, and dynamically collecting the three-dimensional coordinates of the detected unmanned aerial vehicle; the initial position and angle parameters of the detected unmanned aerial vehicle are collected and recorded in real time through the terminal; the wind field equipment is started, and the wind field equipment outputs different wind speeds and angle changes; the terminal collects and records angle change parameters of the gyroscope of the detected unmanned aerial vehicle in real time, and the terminal calculates target indexes and outputs detection data. The method is mainly used for detecting the wind resistance of the unmanned aerial vehicle.

The technology relates to measurement systems and methods for measure kinematic data of an athlete during athletic activities. In an example, the system includes a housing that includes an accelerometer and a gyroscope; at least one processor; and at least one memory. The system performs operations including generating kinematic data for the athlete during the athletic activity; detecting an occurrence of a feedback trigger condition; surfacing a feedback request for a natural language response from the athlete during the athletic activity; receiving a natural language response from the athlete during the athletic activity; generating an athlete-response prompt for a generative artificial intelligence (AI) model; providing the athlete-response prompt as input to the generative AI model; receiving, from the generative AI model in response to the athlete-response prompt, a standardized tag for the defined categories; and tagging the kinematic data with the standardized tag.

Aspects of the present disclosure relate to a process flow for fabricating a waveguide structure having a silicon nitride core with atomic-scale smooth sidewalls achieved by wet etch (rather than traditional dry etch treatment). The mask is pre-biased to account for lateral etching during the wet etching step.

A process for manufacturing a combined microelectromechanical device envisages: forming, in a sensor wafer, at least a first and a second microelectromechanical structures, at a main surface; forming, in a cap wafer, at least a first and a second cavities, at a respective main surface; forming a getter region inside the first cavity; bonding the main surfaces of the sensor and cap wafers by means of a bonding region, to define a first and a second hermetic environments for the microelectromechanical structures at different pressure values. A raised frame is formed, before the bonding step, in such a way as to be located around the first cavity; the bonding region determines the bonding of the sensor and cap wafers at the raised frame and the definition of the first hermetic environment associated with the first cavity, in a time interval prior to hermetic closure of the second cavity.