37results about "Anti-hunting elements" patented technology

A motor control device includes a signal identifying unit and an overvoltage detecting unit. The signal identifying unit includes an optical isolator that converts an electrical signal supplied via a terminal to which an external device is connected and a switch that turns off a connection circuit connected to the terminal. The overvoltage detecting unit is configured to turn off the switch when a voltage applied to the connection circuit is greater than a threshold voltage.

In ERIT, it is necessary to set a reference model for generating a target command for an ideal response before FF control design, and if an appropriate reference model cannot be set, coupled vibration caused by a plurality of structures cannot be suppressed. Further, when the characteristics of the plant are partially or entirely unknown, it is practically impossible to provide an appropriate reference model. Therefore, an object of the present invention is to provide a design method and a design device for data-driven damping feedforward control that can eliminate the need to set a complicated reference model.SOLUTION: A feedforward control design method has a controller structure in which a plurality of feedforward controllers to be designed are provided, a denominator polynomial of each feedforward controller is common, and a numerator polynomial is a free parameter, and the free parameter is designed by solving an optimization problem for minimizing a deviation between a target command generated by one feedforward controller among the plurality of feedforward controllers and a predicted response.SELECTED DRAWING: Figure 2

Inventive concepts herein relate to mitigating phase current oscillations and vibrations in a spinning, lightly loaded three-phase electric motor. A motor starter can transition between various acceleration profiles defined by unique firing angles and / or firing angle rates of change. These transitions adjust the firing angle of thyristors, which directly manage each phase of a three-phase power supply to the motor. The motor start can identify when a motor has residual motion from prior operation and can modulate the firing angle and / or firing angle rate of change accordingly to reduce a duration of time that issues such as phase current oscillations or vibrations might occur.

Method for heating a coolant of an electrical traction machine of a motor vehicle, the electrical machine including, in addition to the coolant, a stator including a polyphase winding, the stator being in heat exchange with the coolant, a rotor, and an inverter / rectifier supplying power to the polyphase winding. The inverter / rectifier includes a plurality of switching cells controlled by a control device. The control device of the inverter / rectifier is configured to control the switching cells so as to short-circuit the polyphase winding in predetermined conditions for the purpose of heating the coolant.

A continuously adjustable valve (10) with a valve slide (14) which can be displaced by an actuator (18) in a valve housing (12) and with an electronic control unit (16; 116) which controls a pressure regulator (2) for determining a control deviation (Δp) between an internal setpoint pressure (p) is revealed. soll int ) and an actual pressure (p ist The pressure regulator (2) controls a setpoint (6) for the actuator (18) depending on the pressure control deviation (Δp). A minimum value generator (1) is used to determine the internal setpoint pressure (p). soll int ) by selecting the lower value of an external target pressure (p) soll ext ) and on the other hand a system pressure (p sys ) is planned. A corresponding procedure has also been disclosed.

A camera module according to an embodiment includes a camera housing, a lens assembly including a lens, at least a portion of the lens assembly is disposed in the camera housing, a first carrier to which the lens assembly is coupled and that is movable relative to the camera housing in a direction of an optical axis of the lens, a second carrier on which the first carrier is coupled and that is movable relative to the camera housing in one or more directions perpendicular to the optical axis, a first piezoelectric motor that is connected to the first carrier and the second carrier and that provides a first driving force to move the first carrier in the direction of the optical axis, and a second piezoelectric motor that is connected to the camera housing and the second carrier and that provides a second driving force to move the second carrier in the one or more directions perpendicular to the optical axis.

A characteristic calculation device (10) that comprises: a sensor information acquisition unit (20) that acquires position information that indicates the position of a motor (70) as detected by a position detector (71) and acceleration information that indicates the acceleration of a mobile part (80) that is connected to the motor (70) as detected by an acceleration sensor (81) that is installed on the mobile part (80); and a sensor characteristic calculation unit (30) that, on the basis of the position information and the acceleration information, calculates and outputs at least one of balance information that indicates the coincidence between the detection axis direction of the acceleration sensor (81) and the direction of the acceleration to be detected by the acceleration sensor (81) and detection sensitivity information that indicates the detection sensitivity of the acceleration sensor (81).

This optronic sight for a motorized vehicle, such as an aircraft, marine vehicle, or land vehicle, comprises: a sighting module (13) capable of being moved around a first axis (X) and a second axis (Y) not parallel to the first axis; means (14, 15) for moving the sighting module around the first and second axes; and a feedback loop for controlling a position parameter of the sighting module based on a setpoint, comprising an adaptive feedback controller (16) capable of calculating a command for a controlled device having a critical mode that modifies the device's response. It includes means (23) capable of determining a fundamental frequency of the critical mode that varies according to an operating parameter of the controlled device, the controller (16) being calculated from the fundamental frequency determined to compensate for the anti-resonance or resonance mode. Abstract figure: Figure 5

The invention relates to a power generation method for powering at least one electrical grid of an aircraft using a power generation system, the aircraft comprising two power supply paths, each power supply path comprising an electrical converter and a generator, the power system comprising two regulation units (21a) respectively associated with each power supply path, each regulation unit (21a) comprising a correction module (5), the correction module comprises an integral corrector (CI), the method comprising the following steps performed for the correction module (5): determining a power setpoint (PBP *) from a distribution voltage setpoint (VDC *) and a measurement of the distribution voltage (VDC); determining a divergence indicator (M3) from the gradient (GPBP *) of the power setpoint (PBP *); and resetting the integral corrector (CI) of the adjustment unit (21a) of the power supply path according to the divergence indicator (M3).

A vibration information calculating device (10) is provided with: a sensor information acquiring unit (20) for acquiring time-series position information relating to a motor (70), detected by a position detector (71), and time-series sensor information relating to a movable portion (80) connected to the motor 70 by way of a joint portion (72), detected by a sensor (81) attached to the movable portion (80); and an information calculating unit (30) for calculating, on the basis of the position information and the sensor information, and outputting at least one of vibration presence / absence information indicating the presence or absence of vibrations of the motor (70) and the movable portion (80), vibration frequency information indicating the vibration frequency of the motor (70) and the movable portion (80), and vibration cause system information indicating the cause system of the vibrations of the motor (70) and the movable portion (80).

The invention discloses a model identification and damping control method and system for a network-forming converter, and belongs to the technical field of power systems. The method comprises the following steps: injecting a pre-generated test signal sequence into an active power reference instruction of a network-forming converter to excite a system to generate a dynamic response; response data of the system under excitation of the test signal sequence is collected, and the response data and the test signal sequence form an evolution type time sequence data set; based on the evolution type time sequence data set, an equivalent linear model for describing system dynamics is calculated through a Koopman operator identification method; calculating to obtain a state feedback gain matrix by solving a linear quadratic optimal control problem; generating a damping control signal based on the state feedback gain matrix and system state data acquired in real time, and superposing the damping control signal to a control instruction of the network-forming converter; according to the method, the risk of performance reduction and even instability caused by model mismatch in a traditional method is overcome.

The invention relates to a method for closed-loop control of a controlled variable to a given reference variable, wherein the actual value and / or the measured actual value of the controlled variable is subject to fluctuation effects with a specific periodicity, the controlled variable being readjusted only if a control difference exists between the reference variable and an average value of the actual value of the controlled variable averaged over a periodic time period, wherein the measured values ​​M1 to M n The specific measurement time points t1 to t2 in a specific controller cycle within each periodic period duration are n It is determined that these measured values ​​are related to or correspond to the corresponding actual values ​​of the controlled variable and / or are suitable for determining therefrom a control difference between the reference variable and the average value of the actual value of the controlled variable. According to the invention, at each specific measuring time t1 to t n The invention also relates to a corresponding carrier and a device.

In a method for modifying a control deviation (RA) within the framework of a fixed-value control system of a controlled system (4) with integrating system behavior, a resting module (10) receives the vector control deviation (RA) as an input vector (EV) of input signals (E1-3) and maps this to an output vector (AV) of output signals (A1-3), wherein the resting module (10) is switchable as a system state (26) between a passive (PZ) and active state (AZ) and, in the passive state (PZ), outputs a zero signal as the output signal (A1-3) if the input signal (E1-3) lies within an assigned corridor (K1-3), and otherwise outputs the input signal (E1-3), and switches to the active state (AZ) if an input signal (E1-3) lies continuously within the corridor (K1-3) for a turn-on time (Tein), and the resting module (10) in the active state (AZ) from the input signal (E1-3) generates a test signal (P1-3) and outputs all output signals (A1-3) as zero signals,and switches to passive state (PZ) when a test signal (P1-3) continuously leaves its corridor (K1-3) for longer than a switch-off time (Taus). A rest module (10) with a computing unit (16) for executing the procedure contains an input (12) for the input vector (EV) and an output (14) for the output vector (AV). A control loop (2) with the controller (8) and a comparator (6) for outputting the control deviation (RA) contains the idle module (10) between comparator (6) and controller (8) and receives the control deviation (RA) from the comparator (6) and the controller (8) receives the output vector (AV) as modified control deviation (RM).

The present application relates to a kind of vehicle ride comfort damping tuning method and tuning system, it includes the following steps: based on input voltage control damper's damping variation;Judge whether the acceleration of damper satisfies preset condition, if yes, the damping parameter of damper is output, otherwise the size of input voltage is adjusted to continue the above-mentioned step.This application embodiment provides a kind of vehicle ride comfort damping tuning method and tuning system, since directly adjusting the input voltage of damper can realize the change of damper damping, and then according to the acceleration value of damper, whether the damping of damper is in the optimal state can be judged, without replacing damper in the whole tuning process, the adjustment duration can be substantially reduced, in addition, since the adjustment direction does not need professional judgment, can get rid of the dependence on personal experience, the difference of debugging result is smaller using the same system.Due to be separately additional system, can be used repeatedly at one time, only need to detect the accuracy of adjustment periodically.

The invention relates to a method (100) for operating a drive system (50) with an open-loop control unit (70) that has at least one first closed-loop controller (10). The drive system (50) forms a closed-loop control path (30) that belongs to the first closed-loop controller (10). The method (100) comprises a first step (110) in which the first closed-loop controller (10) is operated in an active operating state, wherein at least one first closed-loop controller input variable (12) is supplied and at least one first closed-loop controller output variable (14) is output. The method (100) also comprises a second step (120), in which a system model (40) is operated that replicates the behaviour of the closed-loop control path (30), wherein a disruptive function (41) is supplied. The method (100) also has a third step (130), in which a first system model output signal (42) is determined, which is combined with the first closed-loop controller output variable (14) to form a closed-loop control path input variable (16). The invention also relates to a computer program product (60) that can be used to carry out such a method (100) and an open-loop control unit (70) that is equipped with such a computer program product. The invention further relates to a correspondingly designed industry application (80).

The present invention discloses a rotary damping automatic control system for a ship manipulator, which relates to the field of rotary damping automatic control and is connected to a server. The server includes a terminal calculation module, an image module, a measurement module, and an execution control module. The present invention determines and analyzes the dynamic image information of the area where the ship is located to obtain the ship dynamic value, determines and analyzes the image information of the ship and the manipulator under static conditions, and accordingly conducts a static analysis of the ship operation to obtain the static required value of the ship operation. Then, by analyzing and processing the wave image information, the water flow image information under the ship environment, and the wind speed information, the environmental dynamic difference value of the ship is obtained, and then the comprehensive abnormal state value of the ship is analyzed. Through analysis and matching, the rotary damping force values corresponding to the comprehensive abnormal state values of different ships are obtained, realizing the automatic control of the rotary damping. It can consider the static and dynamic states of the ship, the characteristics of the manipulator, and the environmental information of the ship's navigation, providing guarantee for the automatic control of the ship's rotary damping.

The present disclosure provides a method and a device for accurately determining a driving level of overdrive by accurately determining a reference luminance for measuring an overshoot degree of a display device. The present disclosure provides a device and a method for accurately determining the driving level of the overdrive by accurately determining the reference luminance using only a rise slope before overshoot occurs and an overshoot slope purely contributed by the overshoot when measuring the overshoot degree.

A method for operating an electric drive system is provided. For example, a controller retrieves from memory a predictive model indicating a predicted winding temperature associated with a known negative temperature coefficient (NTC) temperature, wherein the predictive model is based on historical NTC temperatures and historical winding temperatures, and one or more operating parameters. The controller receives current NTC information indicating one or more current NTC readings corresponding to one or more switching devices within the inverter. The controller determines an estimated winding temperature corresponding to the motor based on the predictive model and one or more current NTC readings and the current operating parameters. The controller provides instructions based on the estimated winding temperature to adjust the motor input.

The present invention belongs to the field of flight control technology, and specifically relates to an aircraft warning method, system, device and computer-readable storage medium based on flight quality, aiming to solve the problem of the lack of real-time risk prediction capability of aircraft. The method of the present invention includes: establishing a longitudinal dynamic model of the aircraft; determining the longitudinal short-period frequency of the aircraft based on the model; determining the longitudinal short-period damping ratio of the aircraft based on the flight quality; constraining the longitudinal short-period frequency based on the longitudinal short-period damping ratio; generating the desired control parameters of the aircraft based on the constrained longitudinal short-period frequency; and issuing a warning based on the desired control parameters. The present invention can convert the longitudinal dynamic characteristics of the aircraft into quantifiable desired control indicators, and realize abnormal warning of flight quality through real-time comparison; improve the comfort and accuracy of the pilot's operation, reduce the probability of unsafe events in the aircraft, provide a scientific monitoring method for the safe operation of the aircraft, and improve the safety of the aircraft.

Method (100) for controlling a drive by means of a control loop (302) assigned to the drive, wherein the drive has a motor (312) and a transmission (322) driven by the motor (312), comprising: detecting an actual motor current value (314) of the motor (312); determining a current stiffness value (354) of the transmission (322) based on the actual motor current value (314) and a stiffness characteristic curve of the transmission (322); determining an actual natural frequency of the drive based on the current stiffness value (354); and changing a parameter of the control loop depending on the actual natural frequency.

A characteristic calculation device includes a sensor information obtainer that obtains position information indicating a position of a motor as detected by a position detector, and acceleration information indicating an acceleration of a movable part connected to the motor as detected by an acceleration sensor attached to the movable part; and a sensor characteristic calculator that calculates and outputs at least one of balance information or detection sensitivity information, based on the position information and the acceleration information, the balance information indicating a degree of matching between a direction of an axis of detection by the acceleration sensor and a direction of acceleration to be detected by the acceleration sensor, the detection sensitivity information indicating a detection sensitivity of the acceleration sensor.

The invention relates to a method (100) for operating a drive system (50) with an open-loop control unit (70) that has at least one first closed-loop controller (10). The drive system (50) forms a closed-loop control path (30) that belongs to the first closed-loop controller (10). The method (100) comprises a first step (110) in which the first closed-loop controller (10) is operated in an active operating state, wherein at least one first closed-loop controller input variable (12) is supplied and at least one first closed-loop controller output variable (14) is output. The method (100) also comprises a second step (120), in which a system model (40) is operated that replicates the behaviour of the closed-loop control path (30), wherein a disruptive function (41) is supplied. The method (100) also has a third step (130), in which a first system model output signal (42) is determined, which is combined with the first closed-loop controller output variable (14) to form a closed-loop control path input variable (16). The invention also relates to a computer program product (60) that can be used to carry out such a method (100) and an open-loop control unit (70) that is equipped with such a computer program product. The invention further relates to a correspondingly designed industry application (80).

The invention belongs to the technical field of flight control, particularly relates to an aircraft early warning method, system and device based on flight quality and a computer readable storage medium, and aims to solve the problem that an aircraft lacks real-time risk prediction capability. The method comprises the following steps: establishing a longitudinal dynamic model of the aircraft; determining the longitudinal short-period frequency of the aircraft according to the model; determining a longitudinal short-period damping ratio of the aircraft according to the flight quality; restraining the longitudinal short-period frequency based on the longitudinal short-period damping ratio; according to the constrained longitudinal short-period frequency, an expected control parameter of the aircraft is generated; and performing early warning based on the operation expectation parameters. According to the method, the longitudinal dynamic characteristics of the aircraft can be converted into quantifiable control expectation indexes, and flight quality abnormity early warning is realized through real-time comparison; the operation comfort and accuracy of a pilot are improved, the occurrence probability of unsafe events of the aircraft is reduced, a scientific monitoring means is provided for safe operation of the aircraft, and the safety of the aircraft is improved.

The embodiment of the invention provides a power system damping controller setting method and system based on artificial intelligence, and belongs to the technical field of damping controller setting. The method comprises the steps that power grid operation data and energy storage unit operation data are collected, a state vector is input into a deep reinforcement learning model, the deep reinforcement learning model outputs the parameter adjustment amount of a damping controller, and the proportional gain and the integral gain of the damping controller are updated according to the parameter adjustment amount; a control instruction used for adjusting active power output of the energy storage unit is generated through the outer-layer damping adjusting ring and the inner-layer energy compensation ring; and calculating a reward value based on the power system response, updating the deep reinforcement learning model according to the reward value, and realizing adaptive setting of the damping controller. According to the invention, the adaptive optimization setting of the parameters of the damping controller is realized through the deep reinforcement learning model; and power oscillation suppression and energy storage energy self-balancing are cooperatively realized by combining a double-layer control loop, so that the transient stability and toughness of a power system are remarkably improved.

A vehicle includes a system that performs a method of derating a motor of the vehicle. The system includes a timer and a processor. The processor is configured to start the timer when a temperature of a stator of the motor exceeds a high temperature threshold, select a blend ratio based on a time value on the timer, determine, using the blend ratio, an intermediate derating curve for the motor by interpolating between a first derating curve associated with a first target temperature and a second derating curve associated with a second target temperature greater than the first target temperature, and derate the motor along the intermediate derating curve.

The invention relates to an electrical generation method for supplying power to at least one electrical network of an aircraft using an electrical generation system, the aircraft comprising two power supply paths, each power supply path comprising an electrical converter and an electrical generator, the electrical system comprising two regulation units (21a) respectively associated with each power supply path, each regulation unit (21a) comprising a correction module (5) comprising an integral corrector (CI), the method comprising steps consisting, for the correction module (5), in: determining a power setpoint (PBP*), from a distribution voltage setpoint (VDC*) and from a measurement of the distribution voltage (VDC), determining a divergence indicator (M3) from a gradient (GPBP*) of the power setpoint (PBP*), and resetting the integral corrector (CI) of the regulation unit (21a) of the power supply path depending on the divergence indicator (M3).