8 results about "Rate gyro" patented technology

A method for controlling a wind turbine is provided. The method includes receiving, via a control system, at least one speed measurement from at least one sensor on a driveline of a wind turbine. The method also includes receiving, via the control system, at least one rate gyroscope speed measurement from at least one rate gyroscope on a driveline of the wind turbine. The method further includes calculating, via the control system, an offset with respect to the at least one rate gyroscope speed measurement as a function of the at least one speed measurement. The method also includes adjusting, via the control system, the at least one rate gyroscope speed measurement by the offset. The method further includes performing, via the control system, a control action on the wind turbine based on the adjusted at least one rate gyroscope speed measurement.

The invention provides an on-line self-adaptive suppression method for self-excited oscillation of a vertical carrier rocket, and belongs to the field of carrier rocket control, aiming at a self-excited oscillation phenomenon occurring in a target range test when the carrier rocket is in a vertical state. The three channels of the vertical carrier rocket are subjected to attitude control by adopting a PD control loop according to attitude angle deviations and rate gyroscope signals respectively, and the rate gyroscope signal of each channel entering the PD control loop is subjected to filtering processing by adopting a self-adaptive wave trap, so that the rate gyroscope signal of each channel entering the PD control loop is obtained. The method is used for reducing elastic vibration signals in control loop angular rate signals and servo swing angle instruction signals. According to the invention, the self-oscillation phenomenon in the vertical state target range test of the carrier rocket can be effectively solved, the influence of the periodic jitter of the carrier rocket on the rocket loading product is eliminated, and the rocket ground test and take-off safety are effectively ensured.

This invention provides a dual-redundancy method for measuring aircraft attitude. It establishes a first measurement channel for the aircraft's heading angle by jointly measuring and calculating with a triaxial accelerometer and a Hall effect magnetometer. A second measurement channel for the heading angle is then established using a MESE rate gyroscope and a MESE angle gyroscope. The errors from these two channels are then combined and nonlinearly transformed, and the error is fed back to the rate gyroscope for secondary measurement correction. Finally, the combined aircraft attitude measurement signal is obtained through integration. Furthermore, when the triaxial accelerometer, magnetometer, rate gyroscope, or angle gyroscope malfunctions, information from the normally functioning sensors is used, and the gain of the combined measurement feedback channel is switched on and off to form a dual-redundancy measurement, thus improving the reliability and accuracy of the overall attitude measurement.

The invention discloses an active load shedding control method based on adaptive gain, and the method comprises the steps: considering the overall parameters of a carrier rocket, neglecting the influence of secondary factors according to the characteristics of a load shedding problem, and building a small-disturbance linearization model of the carrier rocket based on a small-deviation linearization hypothesis; according to the small disturbance linearization model, utilizing the output of the inertial measurement unit platform and the rate gyroscope to obtain the measurement values of the attitude angle, the attitude angular velocity and the apparent acceleration of the carrier rocket; designing an attitude tracking controller by adopting a PD control method according to the attitude angle and the attitude angular velocity measurement value; and according to the apparent acceleration measurement information, identifying to obtain an aerodynamic acceleration value, realizing active load shedding, and designing an attitude tracking and load shedding controller. And designing a load shedding control gain adjusting strategy for active load shedding control gain in the attitude tracking and load shedding controller according to the actual value, the nominal value and the historical peak value of the pneumatic acceleration, and dynamically adjusting the size of the active load shedding control gain.

The application provides an inverted pendulum control method adopting inversion sliding mode PID hybrid switching, which measures the swing angle of the inverted pendulum by installing a micro gyroscope and measures the swing angular velocity by installing a rate gyroscope; then, a nonlinear integral is adopted to obtain integral signals of the swing angle error and the swing angular velocity error and a sliding mode integral signal; then, a second-order delay device is adopted to solve the swing angle expected differential signal, the swing angle error differential signal, the swing angular velocity error differential signal and the sliding mode differential signal through a transfer function; finally, three methods of inversion self-adaption, sliding mode self-adaption and improved PID are adopted to design the inverted pendulum control law, and switching control is carried out based on different ranges of the swing angle error, so that the sliding mode control is adopted when the error is large, the inversion control is adopted when the error is medium and the PID control is adopted when the error is small, thereby the advantages of the three kinds of controls can be combined and the quality of the inverted pendulum control is improved.

The presently disclosed subject matter includes a system and method dedicated to mitigating inertial measurement unit (IMU) axis failures. The system comprises processing circuitry operatively connectable to an IMU including accelerometer and rate gyro subsystems configured to provide real-time IMU data along multiple axes. The processing circuitry is configured to monitor the real-time IMU data and detect a fault affecting at least one IMU axis. Responsive to detecting the fault, a machine learning model trained on relationships between IMU measurements is applied to reconstruct missing or degraded accelerometer or rate gyro data based on remaining available IMU data, thereby generating reconstructed IMU data representative of platform motion.

The application obtains the line-of-sight angle signal of the accurate guidance photoelectric guidance platform by adopting the IRFPA infrared camera to take pictures and measure and carries out data processing, and obtains the platform angular velocity expected limiting signal by non-linear operation, lag and integral, design of non-linear adaptive advance correction network and limiting, and installs the rate gyro to measure the pitch angular velocity signal of the photoelectric guidance platform, and obtains the platform angular velocity error signal by comparison; the rate gyro is installed on the base of the photoelectric guidance platform to measure the platform base pitch angular velocity signal, and the base non-linear feedforward compensation signal is obtained by designing the non-linear feedforward compensation network; finally, the angular velocity error advance correction signal is obtained by designing the interference adaptive compensation and non-linear advance correction network, and the final photoelectric guidance platform stable control voltage signal is formed by superimposing the platform angular velocity error signal to realize the stability of the accurate guidance photoelectric guidance platform.

The invention provides a knowledge data hybrid-driven rate gyroscope accurate health state assessment method. The method comprises the following steps: step 1, acquiring rate gyroscope data; 2, designing a key index according to the output information of the rate gyroscope as the input of a belief rule base BRB; 3, constructing a confidence rule base; 4, performing online reasoning on the BRB model; 5, training data label conversion; step 6, BRB model parameter optimization: through an optimization process, the model can automatically adjust parameters according to historical data so as to improve the accuracy and reliability of rate gyroscope health state evaluation; according to the method, a confidence rule base model combining expert knowledge and historical data is provided, the problem of data volume imbalance is effectively solved by fusing multi-modal data and expert experience, the model is trained by adopting a gradient descent optimization algorithm, and the accuracy of health state assessment is improved.