75 results about "Active vibration control" patented technology

The invention provides a vibration active control method based on a secondary channel online identification FxLMS algorithm, a vibration active control system comprises a sensor, a vibration signal conditioner, an actuator, a piezoelectric power amplifier, a real-time control simulation system and a computer, and a built SPMFxLMS algorithm physical model is embedded in a computer controller. The SPMFxLMS algorithm physical model comprises a vibration response error signal calculation module, a control channel adaptive filter, an identification channel adaptive filter and an unknown secondary channel model, and the unknown secondary channel model is constructed according to the identification channel adaptive filter and updated in real time. The algorithm physical model constructed by the invention adopts an improved power scheduling strategy and an identification adaptive filter to update and calculate the vibration response time domain data of the controlled object, so that the obtained control voltage signal is reliable, the residual vibration quantity caused by identification noise is avoided, the vibration suppression effect is excellent, and the method has excellent noise immunity and applicability.

According to the present invention there is provided an active vibration control system comprising: an electromagnetic actuator and a control element, the electromagnetic actuator being operable to apply a force on a base structure to which the active vibration control system is attachable such that vibrations of the base structure are actively controllable by the application of said force, wherein the electromagnetic actuator and control element are relatively moveable such that the active vibration control system has at least two modes of vibration, and wherein movement of the electromagnetic actuator causes movement of at least a part of the control element.

The invention relates to the technical field of vibration active control and artificial intelligence, and discloses an aero-engine fan rotor keyless phase virtual dynamic balance method and system based on a finite element method, and the system comprises a modeling and simulation module which is configured to obtain the first-order critical speed and vibration mode of an initial rotor dynamics simulation model; the model calibration module is configured to calibrate the initial rotor dynamics simulation model according to the first actual amplitude to obtain a calibrated rotor dynamics simulation model; the model updating module is configured to update the calibration rotor dynamics simulation model to obtain an updated rotor dynamics simulation model; and the trial weight and counterweight module is configured to substitute the second actual amplitude into particle swarm optimization, calculate the actual total unbalance amount of the rotor system and the trial weight angle difference, and finally add a counterweight and select a direction until the vibration is reduced to realize dynamic balance. According to the invention, the position of the unbalance can be accurately determined only through amplitude analysis.

The present invention provides a tuned liquid column damping and vibration reduction system for floating wind power. The system is arranged inside the wind turbine tower. Four groups of guide rails are arranged on the inner wall of the wind turbine tower, and an annular bottom plate is arranged at the lower side. A spring base and a spring are arranged on the annular bottom plate. The upper part of the spring is provided with a tuned liquid column ball damper riser, and a pulley block is located on the guide rail. The bottoms of the tuned liquid column ball damper risers are installed with a cross-shaped tuned liquid column ball damper horizontal pipe to communicate. A ball valve is installed in the middle of the tuned liquid column ball damper horizontal pipe, and a one-way double-opening valve, a valve position limiter, a switch valve, and a pressure sensor are installed in the middle of the branch pipe. A vibration sensor is installed at the top of the wind turbine tower. The system dynamically adjusts the natural vibration frequency of the system by coordinating the working liquid flow in the tuned liquid column ball damper riser and the tuned liquid column ball damper horizontal pipe, has the effect of three-dimensional semi-active vibration control, solves the problems of narrow frequency band and single control direction of the traditional system, and is more suitable for use in complex marine environments.

The invention discloses a multi-degree-of-freedom staggered active vibration absorption method and system, photoetching equipment and a storage medium. The method comprises the following steps: acquiring vibration data; determining vibration state parameters of each degree of freedom at the current moment based on the vibration data; on the basis of the vibration state parameters, according to a preset interleaving control strategy, control instructions for a plurality of actuator units are generated; and driving the actuator unit to generate corresponding active damping force based on the control instruction. The embodiment of the invention aims to overcome the technical defects of potential instability, high energy consumption and poor time-varying disturbance adaptability caused by control resource competition in a traditional multi-degree-of-freedom active vibration control system, so that more stable, more efficient and more adaptive vibration suppression is realized.

A multi-harmonic, multi-channel, global active vibration control method for helicopters involves constructing independent bandpass tracking filter banks to separate the harmonic components in the acceleration response error signal at each control point on the helicopter's fuselage. Each harmonic component is independently controlled by selecting a convergence factor. During the control process, the reference input signal is reconstructed while updating the weights of the Fx-LMS adaptive controller with global vibration minimization as the control objective. This method achieves significant attenuation of the acceleration response at all measurement points on the helicopter's fuselage under multi-harmonic interference from the helicopter's rotor blades, effectively improving the vibration level of the fuselage. The present invention separates and independently controls the fundamental and harmonic components of the vibration signal by constructing several independent adaptive filters, with global vibration minimization as the control objective, to update the controller weights.

A system and method for removing unwanted vibrational noise is provided. The system can detect, by one or more microphones of the system, at least one audio signal that includes audio content output from at least one speaker and audio data from one or more other sources or caused by the one or more other sources. The other audio data can include determined undesired vibrational noise that causes distortion of the at least one audio signal. The system can determine, by at least one sensor of the system, a subset of the other audio data based in part on determining at least one motion of a user of the system or motion of one or more other users. The system can remove or reduce the undesired vibrational noise from the at least one audio signal to enable output of sound associated with the modification of the at least one audio signal.

The invention discloses an active control system and method for vibration of an exhaust pipeline of an air compressor, the system comprises the exhaust pipeline with two rigidly fixed ends, and a signal generator, a power amplifier and a vibration exciter which are sequentially connected along a signal transmission direction, and a vibration excitation head of the vibration exciter acts on a pre-set vibration excitation point on the exhaust pipeline; the laser vibration meter, the data acquisition board and the digital signal processing module are sequentially connected in the signal transmission direction; the digital signal processing module generates a driving control signal for the piezoelectric actuator in real time by adopting a self-adaptive active vibration control strategy based on the collected vibration signal; a laser beam of the laser vibration meter vertically irradiates a measurement point on the surface of the exhaust pipeline, the piezoelectric actuator is arranged at a preset position on the surface of the exhaust pipeline, pipeline vibration is simulated through the vibration exciter, and a control signal is generated in real time by adopting a parallel FxLMS self-adaptive control strategy based on frequency band decomposition of a reference signal; and after power amplification, the piezoelectric actuator adhered to the surface of the pipeline is driven to generate deformation to counteract vibration.

A system and method for removal of unwanted vibration noise are provided. The system may detect, by a microphone(s) of the system, at least one audio signal including audio content output from at least one speaker and other audio data from one or more other sources, or caused by the one or more other sources. The other audio data may include determined undesirable vibration noise causing distortion of the at least one audio signal. The system may determine, by at least one sensor of the system, a subset of the other audio data based in part on determining at least one motion of a user of the system, or motion of one or more other users. The system may remove, or reduce, the undesirable vibration noise from the at least one audio signal to enable output of sound associated with a modification of the at least one audio signal.

An active vibration control device includes: an outer cylinder; an inner cylinder arranged on an inner peripheral side of the outer cylinder; an electromagnetic coil; a first magnetic body and a second magnetic body; a first fluid chamber filled with a magneto-rheological fluid; a second fluid chamber adjacent to the first fluid chamber and filled with a fluid; an outer cylinder flange; and an inner cylinder flange arranged to be separated from the outer cylinder flange in an axial direction, the first fluid chamber and the second fluid chamber are partitioned from each other in the axial direction by a flexible member, the second fluid chamber is formed to be sandwiched between the inner cylinder flange and the outer cylinder flange, and portions of the first fluid chamber form flow passages of the magneto-rheological fluid that are located on a magnetic circuit.

The application discloses an active isolation-passive damping-energy recovery integrated composite isolation wall, belonging to the field of rail transit, comprising a magneto-rheological damping unit, a linear motor displacement control unit, a passive vibration control module, a bottom support element, a top covering module and the like; the magneto-rheological damping unit guarantees controllable damping force of the magneto-rheological damping unit through the magneto-rheological effect of magneto-rheological fluid in a cavity, and actively controls the train track in real time; the linear motor displacement control unit accurately adjusts the system displacement, and realizes active vibration control; the passive vibration control module realizes efficient vibration energy attenuation through cooperation of various elements; the bottom support element provides bearing and stable support, and the top covering module has vibration monitoring and vibration energy conversion and protection functions. The isolation wall combines real-time adjustment of active control and energy dissipation of passive control, constructs a multi-stage vibration control strategy, adapts to different vibration environments, and improves the stability and safety of the rail system.

The application provides an active vibration control system and method. By collecting displacement, velocity and acceleration information of the lifting rod, the transverse moving rod and the overturning shaft, and synchronously collecting the amplitude of external vibration disturbance acting on the trolley structure; based on the connection mode of the trolley rod, the joint friction characteristics, the component inertia parameters and the coupling torque parameters between joints, a multi-degree-of-freedom mechanical model of the trolley is established or updated; the real-time state input of the state collection step is input into the mechanical model, the coupling vibration amplitude of each degree of freedom under the current disturbance is calculated, and vibration evaluation is performed; a multi-axis cooperative control algorithm is used to determine a set of coordinated control quantities for reducing the coupling vibration amplitude; the control quantities obtained in the control quantity generation step are output to the lifting rod, the transverse moving rod and the overturning shaft at the same time to drive the coordinated action of each degree of freedom to suppress vibration, so that the vibration amplitude of the corbel formwork trolley is kept within the preset vibration threshold.

The invention discloses an embedded active vibration control device and method based on a heterogeneous multi-core architecture, the core of the device is a heterogeneous multi-core processor, and the device comprises a real-time processing core and an application processing core; and respectively operating a real-time system and a universal operating system which are isolated from each other. The real-time system uninterruptedly executes core control tasks such as vibration signal acquisition, vibration suppression calculation and output at a fixed period; the general operation system is responsible for non-real-time functions such as human-computer interaction, communication and high-performance calculation; the two cores share data through an inter-core communication mechanism to realize function collaboration. Compared with the prior art, the hybrid key deployment architecture is adopted on the single heterogeneous multi-core processor, so that high-determinacy real-time vibration control and complex non-real-time function collaboration are realized, and the absolute reliability of a core control task is ensured.

The invention discloses a data driving type control method for vibration suppression of a flexible mechanical arm, and relates to the technical field of robot control, and the method comprises the following steps: constructing a feedback control system for vibration suppression at the tail end of the flexible mechanical arm, and taking periodic residual vibration collection information of a tail end vibration sensor as driving data; designing an adjustable feedback controller corresponding to the control system, and obtaining a feedback control system for realizing residual vibration minimization through adjustable parameter optimization of the adjustable feedback controller; a self-adaptive parameter optimization algorithm is developed to achieve the purpose of minimizing tail end residual vibration, and the developed algorithm carries out real-time optimization on a feedback controller based on driving data; the limitation of an existing active vibration control method is broken through, the tail end residual vibration can be effectively restrained only by depending on the real-time acquisition and measurement signals of the tail end vibration sensor of the flexible mechanical arm as driving data of the control system, and the complete data driving flexible mechanical arm vibration control method is achieved.

The invention discloses a vibration active control method based on a PPO-HAFxLMS algorithm, and relates to the field of vibration active control. The method comprises the following steps: determining a target vibration frequency band needing to be suppressed and a vibration attenuation standard so as to determine configuration of related hardware in the vibration active control system; capturing an external disturbance signal received by the controlled object; and on the basis of the time domain data of the external disturbance signal, a required control voltage signal is generated in real time by using a PPO-HAFxLMS algorithm, and vibration suppression is realized. According to the method, on the basis of a traditional FxLMS algorithm, a feedback channel is added to form a HAFxLMS algorithm, filter coefficients and step length updating are optimized through the HAFxLMS algorithm, the step length and the weight of a filter are dynamically adjusted according to the correlation between error signals and input signals and the change of the environment through a PPO reinforcement learning algorithm, and therefore the convergence speed and the steady-state error of vibration control are optimized, and the stability of vibration control is improved. And the vibration suppression effect is obviously improved.

This invention proposes a secondary channel modeling method for a vibration active control system based on a top-mounted rotor hub. The method includes: activating the actuator of the vibration active control system when the rotor hub is not rotating, outputting actuating forces in both directions. These forces serve as load inputs to the test bench. The actuating forces are transmitted via a path that sequentially passes through the rotor hub actuator mounting location, the collector ring, the shaft, the spring, and the base, ultimately reaching the vibration sensor mounting location. The vibration sensor collects the vibration response at this location, identifying the secondary channel transfer function matrix in the fixed state. The secondary channel transfer function matrix is ​​then substituted into the output force transmission relationship formulas for the fixed and rotating states to obtain the initial value of the secondary channel model in the rotating state. Using this initial value, an adaptive algorithm is used as the physical model for online identification of the secondary channel, enabling online modeling of the system's secondary channels under rotor hub rotation conditions. This method allows for online iterative construction of time-varying secondary channel models, resulting in high modeling efficiency.

The invention provides a flexible sailboard satellite active vibration control method and device for SADA disturbance, and belongs to the field of spacecraft attitude determination and control. The method solves the problem of stability caused by frequency drift in the prior art and the problem that the method depends on a satellite model and cannot adapt to a time-varying system. The method comprises the following steps: acquiring an SADA driving angle, an angular velocity of a fiber-optic gyroscope and voltage data of a piezoelectric sensor; performing discrete short-time Fourier transform on the voltage data to obtain an amplitude spectrum and a phase spectrum; identifying the frequency corresponding to the peak value of the amplitude according to the amplitude spectrum, and associating the SADA driving angle corresponding to the peak value with the angular velocity of the fiber-optic gyroscope; the stability of the whole satellite is judged according to the angular velocity of the fiber-optic gyroscope, and when the angular velocity exceeds a set threshold value, control parameters of the piezoelectric actuator are adjusted in a segmented mode; and iteratively executing the steps until the stability of the whole satellite meets the index requirement. The method is mainly used in satellite control field.

The invention provides a rotor phase regulation and control method for active vibration control of a multi-rotor aircraft. The rotor phase regulation and control method is characterized by comprising a multi-rotor phase coordination strategy, an active control method and a rotor phase regulation and control algorithm. Active coordination of multi-rotor phases is realized through independent control of different paired dual-rotor phases and phase differences between the paired two rotors; establishing a control channel model from rotor loads to control points, taking three-way weighted vibration acceleration at the control points as a control target, and adopting an optimal control strategy to optimize multi-rotor phase control parameters; multi-rotor phase optimal regulation and control are realized through a rotating speed planning strategy, so that the vibration level of the multi-rotor aircraft is effectively reduced, and the comfort and reliability of the multi-rotor aircraft are improved.

This invention discloses an interactive multi-model adaptive active vibration control method based on variational Bayesian methods, belonging to the field of vibration control technology. The method includes establishing a system model set containing multiple potential dynamic modes and initializing each model; performing variational Bayesian iteration on each model within each control sampling period; repeating the above process for each channel to obtain the optimal state estimate for each channel; fusing the state estimates of multiple channels using a covariance cross-fusion method to calculate the global optimal state estimate; convolving the global optimal state estimate with a reference signal filtered by the secondary channel model to generate an inverse control signal, which drives an actuator via a power amplifier to produce a secondary force that counteracts the original vibration, thus achieving vibration suppression. This invention achieves high-precision and highly robust vibration suppression by fusing variational Bayesian adaptive Kalman filtering with interactive multi-model estimation.

The application relates to the technical field of electromagnetic actuators, and discloses an electromagnetic environment optimization method for an actuator, computer equipment, a computer readable storage medium and a computer program product, to solve the problem of poor active vibration control effect. The method comprises the following steps: acquiring main technical index requirements of an electromagnetic actuator; establishing an initial actuator structure model according to initial values of active output force influencing factors and the main technical index requirements of the electromagnetic actuator; determining target ampere-turns of coil current excitation based on the initial actuator structure model; and determining target cross-sectional areas of the coil, target winding lengths, target distances between the armature and the surface of the permanent magnet, and obtaining a target actuator structure model based on the initial actuator structure model and the target ampere-turns of the coil current excitation. The method can make the electromagnetic actuator have the characteristics of small volume, relatively small working current, linear stability, relatively low power consumption, large active output force and strong output force density.

The application provides a stability test method for a helicopter hub top-mounted vibration active control system. The method comprises the following steps: determining a stability test item, wherein the stability test item comprises a constant-speed system stability test, a variable-speed system stability test, a dangerous-speed-range stability test and an actuator power-off stability test. The constant-speed system stability test is used to simulate a constant-speed working state of a helicopter hub and to check whether the hub top-mounted vibration active control system is stable. The variable-speed system stability test is used to simulate a variable-speed working state of the helicopter hub and to check whether the hub top-mounted vibration active control system is stable. The dangerous-speed-range stability test is used to obtain an inherent frequency of a coupled rotor system formed after the hub top-mounted vibration active control system is installed on a test device and to check whether the coupled rotor system is stable when passing through the inherent frequency. The actuator power-off stability test is used to simulate an actuator power-off fault and to check whether the hub top-mounted vibration active control system is stable. The method can effectively check the stability of the hub top-mounted vibration active control system.

The invention discloses a rigid-flexible coupling dynamics modeling method based on a rigid-flexible coupling spacecraft and application, and belongs to the technical field of spacecraft dynamics and control. The method comprises the following steps: S1, in a floating coordinate system, determining a deformation displacement vector of any point P on a neutral axis OBP of the flexible accessory; s2, determining a position vector and a deformation displacement vector of any point Q0 on the flexible accessory; and S3, constructing a rigid-flexible coupling dynamic model of the rigid-flexible coupling spacecraft. According to the method, a single-frame control moment gyroscope is used as a vibration suppression execution mechanism of a flexible accessory, and a rigid-flexible coupling dynamic model is discretized and then used for attitude control of a rigid-flexible coupling spacecraft and design of an active vibration control system. According to the method, an analysis basis and a dynamical model support are provided for efficiently suppressing the vibration of the large flexible structure of the spacecraft.

The application discloses a kind of multi-degree-of-freedom staggered active vibration absorption method, system, photolithography equipment and storage medium, the method comprises: obtaining vibration data;Based on the vibration data, the vibration state parameter of each degree of freedom at the current time is determined;Based on the vibration state parameter, according to the preset staggered control strategy, the control instruction for multiple actuator units is generated;Based on the control instruction, the corresponding active damping force is generated by driving the actuator unit.The embodiments of the present application aim to overcome the technical defects of potential instability, high energy consumption and poor adaptability to time-varying disturbance caused by control resource competition in traditional multi-degree-of-freedom active vibration control system, so as to realize a more stable, more efficient and more adaptive vibration suppression.

The present invention proposes a robot processing vibration control method and system, belonging to the technical field of robot vibration control. The method includes: decoupling the acceleration of the six-axis at the end to sense the vibration at the end of the robot; establishing a model of the robot joints and the end acceleration, and obtaining the relationship between the load side and the end acceleration through the Jacobian matrix; using a Kalman filter to estimate the joint speed on the load side; designing an active damping controller, analyzing the influence of the disturbing force, establishing a feedback term and introducing a feedforward term to eliminate the steady-state error; compensating the corrected speed in the active damping controller into the speed loop controller to achieve active vibration control. The present invention can accurately sense and control the vibration of a flexible joint robot, without modifying the body, introducing the six-axis acceleration signal at the end to achieve damping adaptive adjustment and improve stability.

This invention discloses an active vibration control system and method for tiltrotor aircraft wings, comprising: an actuator assembly consisting of piezoelectric laminated actuators symmetrically arranged within the wing; acceleration sensors, including a wing acceleration sensor located at the outer end of the wing and a fuselage acceleration sensor located in the cockpit; and an adaptive control unit for acquiring sensor signals and outputting control commands. A dual-loop control and flight state tracking strategy is employed: the first control loop implements dynamic characteristic control for the wing-rotor system to suppress transient responses; the second control loop implements steady-state response control for the airframe structure to suppress steady-state harmonic vibrations at the rotor pass frequency and its integer multiples. The flight mode is determined based on the rotor speed and nacelle tilt angle, and the weights of the dual-loop control are dynamically adjusted. This invention achieves adaptive vibration suppression of the tiltrotor aircraft throughout its entire flight envelope, balancing transient and steady-state response control, improving flight quality and extending the lifespan of critical equipment.

The invention discloses a double-satellite multi-loop cooperative control method based on a non-contact load vibration isolation system. The method comprises the following steps: dividing a whole control system into a satellite platform attitude control loop, a follow-up control loop of a load following satellite platform and a load cabin medium-high frequency vibration suppression loop; determining a follow-up control loop control law of a load following satellite platform; determining a satellite platform attitude control loop control law; determining a high-frequency vibration suppression loop control law in the load cabin; and the requirements of vibration isolation and high-precision rapid pointing adjustment of the load are met through a loop synergistic effect. According to the control method, the multi-time-scale system cooperative control problem of a satellite platform attitude control loop, a follow-up control loop of a load following satellite platform and an active vibration control loop is considered, and the three loops act synergistically, so that the control target of high precision and high stability is achieved.

The invention provides an active vibration control method and device for working condition switching of deep learning and reinforcement learning, and relates to the technical field of vibration control. The method comprises the following steps: aiming at a multi-channel active vibration isolation system, establishing primary and secondary channel models for each channel under different working conditions; constructing an interaction environment corresponding to the working condition, designing a state space, an action space and a reward function, and training to obtain an active vibration control strategy network of different working conditions; establishing a working condition classification network based on a sparse automatic encoder; and according to the collected monitoring data and the working condition classification network identification working condition, obtaining a corresponding active vibration control strategy network output control filter vector, calculating to obtain a control quantity, and realizing active vibration control. According to the method, the problem of control instability of the active vibration isolation system when the secondary channel fluctuates and the problem of control failure in a working condition switching scene are effectively solved, and control strategy self-adaptive matching without manual intervention of switching parameters is realized.

A vibration prediction method for a wind tunnel model support system based on fluid-structure interaction analysis belongs to the field of active vibration control of aircraft models. First, a structural finite element model of the wind tunnel model support system is established based on its three-dimensional characteristics of the support system and the flow field. Secondly, in the fluid domain, the k-epsilon turbulence calculation method is combined to simulate the wind tunnel flow field environment, and the fluid stress and displacement are obtained through fluid dynamics analysis, and then the aerodynamic load of the flow field acting on the solid domain is obtained. Then, in the solid domain, the solid stress and deformation are obtained through transient dynamics analysis. Finally, considering the fluid-structure two-phase coupling effect, combined with the fluid-structure coupling control equation and Fourier transform, the time-domain and frequency-domain vibration responses of the wind tunnel model support system are obtained, and the vibration response prediction of the model support system is realized. The present invention can predict the vibration of the model support system by numerical simulation without conducting wind tunnel tests, avoid risks during the test process, can predict vibrations at different wind speeds and different angles of attack, has high calculation accuracy and good effectiveness, and provides a good basis for the vibration control of the model support system.