77 results about "Rotor speed" patented technology

The application discloses a kind of offshore wind turbine pitch control methods based on predefined time adaptive dynamic programming, comprising: establishing single-pile offshore wind power generator full coupling mathematical model;The single-pile offshore wind power generator full coupling mathematical model includes the motion equation of system and the mathematical model of double-mass transmission system;Using the mathematical model of double-mass transmission system constructs rotor speed tracking error, adopts error adjustment method to process the non-affine characteristic of system, obtains the nonlinear affine model of single-pile offshore wind power generation system in combination with motion equation;The control strategy is constructed as the infinite time domain optimal performance index function of the change of pitch angle;Using predefined time nonlinear disturbance estimator estimates disturbance term in nonlinear affine model;To the equivalent form of Hamilton-Jacobi-Bellman equation of infinite time domain optimal performance index function, the approximate optimal control method based on only evaluation type neural network is used to solve equation to obtain optimal control strategy.

The present application relates to the technical field of aero-engine aerodynamic optimization and computer-aided design, and discloses a numerical optimization design method and structure for aero-engine low-pressure turbine blade leading edge modeling based on response surface modeling. The method realizes precise matching of Klebanoff stripe and large-scale vortex generation timing by adjusting flow or rotor speed to change wake injection angle, and promotes stripe impact and accelerates large-scale vortex breakup. Meanwhile, by constructing a blade leading edge modeling parameterization model and establishing a response surface proxy model for the combination of modeling design variable parameters and boundary layer velocity mean square deviation, the optimal design variable parameter combination is determined in the constraint domain with the maximum velocity mean square deviation in the boundary layer as the target. The present application effectively reduces the boundary layer momentum thickness and total pressure loss under the premise of ensuring constant blade load, improves the design efficiency and engineering applicability under low Reynolds number conditions, and does not need to introduce additional flow control structures, thus being simple in structure and easy to implement.

This invention relates to the field of unmanned aerial vehicle (UAV) control technology, specifically to a tilting rotor omnidirectional UAV control method and related equipment. By acquiring the UAV's current pose information (including position, attitude, and body angular velocity) and desired pose information, the position controller generates a desired total force based on the position deviation, the attitude controller generates a desired angular velocity based on the attitude difference, and the angular velocity controller generates a desired total torque based on the angular velocity deviation, forming a three-level control closed loop. The control distributor uses a rotor configuration dynamics model to convert the total force and torque into desired thrust for each rotor, calculates the desired rotational speed based on the thrust-rotor speed correspondence, and controls the rotor rotation. This scheme achieves decoupling optimization of position and attitude control, improving pose control accuracy and response speed.

This invention relates to the field of unmanned aerial vehicle (UAV) flight control technology, and discloses a method for adaptive adjustment control of UAV flight attitude. Addressing the problems of unstable flight and untimely or inaccurate attitude adjustment of UAVs in complex weather conditions and variable terrain, this method deploys multiple types of sensors on the UAV to collect flight data in real time, including information such as air pressure, wind speed and direction, and attitude angles, and transmits the data to a central processing unit (CPU). The CPU analyzes and processes the data based on a preset algorithm model. When it detects a deviation in flight attitude from a set value, it automatically adjusts the UAV's rotor speed, wing angle, and other actuators to achieve rapid adaptive adjustment of flight attitude. This method effectively improves the flight stability and reliability of UAVs in complex environments and can be widely applied in fields such as aerial surveying, material delivery, and environmental monitoring, ensuring efficient and safe operation of UAVs.

An automatic variable flux axial liquid-cooled motor, relating to the field of motor technology, aims to solve the problems of complex and costly weak flux control in existing motors. The motor includes an upper cover and a lower housing with water channels. The stator is installed inside the lower housing, with its core tightly fitted to the water channels for efficient heat dissipation. The rotor is located above the stator and is slidably connected to the output shaft via a spline, allowing axial sliding and stable torque transmission. Four evenly distributed flyweights are arranged on the upper side of the rotor. A return spring is mounted above each flyweight, and a push rod is attached below. The other end of the push rod rests against a shoulder at the spline end of the output shaft (the shoulder serves both positioning and support functions). During operation, as the rotor speed increases, the centrifugal force of the flyweights increases, and the unfolding angle widens, pushing the push rod downwards and causing the rotor to slide upwards. This increases the air gap between the stator and rotor, increasing leakage flux, reducing magnetic flux linkage and back electromotive force, thereby widening the speed range and improving efficiency. When the speed decreases, the return spring resets the flyweights, and the air gap recovers. This structure integrates automatic flux adjustment and axial liquid cooling functions, offering a simple structure and high efficiency.

The application discloses a double-fed induction generator rotor speed estimation method based on maximum cross-correlation entropy weighting, and belongs to the field of motor control. The method creatively applies cross-correlation entropy theory to noise covariance estimation of EKF, and designs a complete algorithm system containing dynamic weighting, adaptive kernel bandwidth, mixed robust weighting and numerical reinforcement. The progressiveness is reflected in that the method comprehensively solves the shortcomings of traditional methods in response speed, parameter disturbance resistance and non-Gaussian noise resistance. Theoretical proof and comprehensive simulation experiments prove that the method has better estimation accuracy, robustness and reliability in complex industrial environments such as wind power generation.

The application discloses an engine rotor multi-parameter measurement system and method, and the system comprises a first optical comb, a second optical comb, a polarization maintaining optical fiber amplifier, a polarization maintaining optical fiber beam splitter, an integrated polarization maintaining optical fiber ring, an integrated polarization maintaining optical fiber beam combiner, a plurality of high-temperature-resistant optical fiber probes, a high-speed photoelectric detector and a data acquisition and processing system; the pulse repetition frequency of the first optical comb is greater than that of the second optical comb, and the two have a high repetition frequency difference; the plurality of high-temperature-resistant optical fiber probes respectively generate reference light pulses and measurement light pulses; the scanning light pulses emitted by the second optical comb respectively interfere with the plurality of reference light pulses and the plurality of measurement light pulses to generate double-comb interference reference signals and double-comb interference measurement signals; through processing of the reference signals and the measurement signals of each channel, the engine rotor speed, the blade tip clearance, the blade tip timing and the blade vibration parameters are obtained. The application has the advantages of high measurement speed, high measurement accuracy and multi-parameter synchronous measurement.

The application discloses a dynamic sealing structure and design method of a rotor device, and belongs to the field of rotor devices used for fluid mechanics experiments. The structure comprises a rotor inner cylinder, a rotor outer cylinder and a rotor cover plate with an annular partition. The chamber between the rotor cover plate and the upper edge of the rotor inner cylinder is divided into a first gap and a second gap which are axially adjacent by the partition, and a super-hydrophobic coating is sprayed on the solid wall surface between the two gaps and below the second gap to retain a drag-reducing gas film. The two gaps are respectively filled with sealing oil which has different viscosities, is insoluble in water and has a smaller density than water, forming a layered seal. The application also provides a corresponding design method, which optimizes the sealing structure parameters by establishing an additional torque model and setting the constraints of the rotor speed, the sealing oil viscosity and the sealing oil density. T 0> 50 T 3, can effectively prevent fluid leakage and gas intrusion at high speed rotation, and controls the additional torque introduced by the seal to be below 2% of the main torque, thereby significantly improving the accuracy of high-precision fluid friction torque testing.

System and method for sensorless control of an induction motor are disclosed. A flux observer estimates a rotor flux based on stator voltage and current measurement. A low frequency signal injection module generates a flux estimation error signal at low motor speed, while a baseline observer generates a model based flux estimation error signal at medium to high motor speed. A switching mechanism selects between these error signal based on motor condition. A proportional integral regulator and integrator process the selected error signal to estimate rotor speed. A lead compensator adjusts phase during transitions to ensure stability, with a switching signal generator activating the LFSI module when stator frequency falls below a predefined threshold. This control system provides rotor flux and speed estimation across a full range of motor speed by adaptively switching between observers based on operating conditions.

This invention provides a grid-connected control method for a flywheel energy storage system based on a dual-rotor brushless motor, belonging to the field of novel energy storage equipment and motor control technology. The control method includes: using the kinematic equation between the stator magnetic field speed, the speed of the adjusting magnetic ring rotor, and the speed of the permanent magnet rotor as the first constraint; using the synchronization of the adjusting magnetic ring rotor speed with the power grid as the second constraint; determining the stator magnetic field speed as the sole control degree of freedom for adjusting the operating state; performing boundary judgment and correction on the stator magnetic field speed; and adjusting the stator magnetic field speed to make the speed of the permanent magnet rotor and the speed of the flywheel change along a linear invariant trajectory determined by the first constraint, thereby realizing the flywheel energy storage system's control requirements for the power grid. This invention has a clear control structure and well-defined constraint relationships, enabling multiple grid-connected support functions while ensuring the safe operation of the flywheel.

Embodiments of the present application provide a six-phase permanent magnet synchronous motor control method, device, equipment and storage medium. The method comprises: obtaining a current rotor speed of the six-phase permanent magnet synchronous motor, and determining a speed interval of the six-phase permanent magnet synchronous motor, wherein the speed interval comprises: a zero-low-speed zone, a transition zone and a medium-high-speed zone; determining a composite control strategy of a high-frequency square wave injection method and a sliding mode observation method according to a weighted composite algorithm and the speed interval, and controlling the six-phase permanent magnet synchronous motor by using the composite control strategy; and performing weighted processing on estimated results of the high-frequency square wave injection method and the sliding mode observation method according to the weighted composite algorithm, the speed interval and the current rotor speed, and then determining a target rotor angle and a target rotor speed. The embodiments of the present application can meet the performance requirements of the six-phase permanent magnet synchronous motor in various speed ranges, accurately obtain the rotor angle and improve the robustness.

This application discloses a motor control method, including: Step A: Alignment control of the rotor, then forced commutation operation of the rotor, and back EMF zero-crossing signal; if a preset number of back EMF zero-crossing signals are continuously detected according to the predetermined commutation sequence, then Step B is executed; Step B: Speed ​​loop closed-loop control of the motor, and after the rotor speed is accelerated to a preset starting speed, back EMF zero-crossing signal is detected; then Step C is executed; Step C: Whenever a back EMF zero-crossing signal is detected, during the period from the detection time of the currently detected back EMF zero-crossing signal to the next commutation time, the drive signal for the motor is stopped, and the electrical angle corresponding to each back EMF is adjusted through the phase-locked loop until the electrical frequency output by the phase-locked loop converges to a target electrical frequency range. Then, the motor is controlled by FOC, avoiding problems such as loss of synchronism and difficulty in starting the FOC sine wave when the motor load torque is large.

This invention discloses a speed regulation method and system based on parameter identification, belonging to the field of motor parameter identification technology. It aims to solve the problem that conventional online parameter identification mechanisms use fixed convergence gains, which deviate from underlying thermodynamic laws, leading to oscillating and unstable speed estimation. The method includes: using the thermodynamic law of conservation of energy to determine the highest possible physical rate of change of the motor stator temperature; setting the physical speed limit boundary of the online parameter identification mechanism; obtaining a dynamic convergence gain with physical boundary awareness; constructing a sliding mode observer with an adaptive identification interface; performing stator resistance parameter identification through the received dynamic convergence gain; and resolving the actual rotor speed of the synchronous motor from the obtained stator resistance identification value to adjust the output power of the circulating water pump. This invention suppresses the oscillation and instability of the stator resistance identification value, ensuring the accuracy of speed analysis of the synchronous motor and the stability of the circulating water pump output power under high-temperature alternating conditions.

The application discloses a kind of vehicle permanent magnet synchronous motor rotary transformer measurement error compensation method, this method comprehensively considers the bias of rotary transformer, amplitude imbalance, three main errors of quadrature imbalance, to this as background, the mathematical model of rotary transformer error is established, error variable is introduced into coordinate transformation, and d, q axis current under the existence of error is deduced, by the subsection integration of d-axis current in each motor electric angle period, the correction value corresponding to three types of errors is extracted in real time, the dynamic compensation of position signal is realized.Simultaneously, the application considers that the current feedback delay caused by the rise of rotor speed and the limited current closed-loop bandwidth, an angle dynamic correction strategy is proposed, to ensure that the algorithm keeps synchronization between integration window and corresponding current phase at high speed, to realize the high-performance compensation of position error in full speed domain.

The application provides a large synchronous motor rotor excitation device and a control method, comprising: a main control unit, which is used for collecting operation parameters of the synchronous motor and calculating a silicon-controlled trigger angle according to a control law; a power unit, which is used for receiving a double-pulse trigger signal and generating an adjustable direct-current excitation voltage; a starting loop, which is used for connecting a starting resistor across both ends of a rotor excitation winding when the motor is started asynchronously; a slip measurement module, which is used for performing AC sampling, digital filtering and slip calculation on a rotor induced voltage signal in an asynchronous starting stage to obtain a rotor speed; a field excitation control module, which is used for sending a field excitation trigger signal to the power unit when the rotor speed reaches a set field excitation speed and a field excitation angle condition is met, so that a three-phase full-bridge rectifier circuit outputs a direct-current excitation current to the rotor winding; a monitoring unit, which is used for parameter setting, state display and fault alarm; an external excitation transformer and an external starting resistor box, which are used for power supply to the power unit and starting current limiting.

The present application relates to side-by-side multi-rotor offshore floating wind turbine rotor aerodynamic coordination system, the system includes: wind speed-wind direction measuring module, for collecting wind speed-wind direction of the whole wind turbine and local wind speed-wind direction of each rotor, obtains first monitoring data;Rotor power generation state monitoring module, for collecting the rotor speed of the main shaft or the shaft end of the generator, and monitoring the power generation, obtaining second monitoring data;Central control module, for judging the wind turbine operating state through the first monitoring data and the second monitoring data, obtaining the judgment result, selecting the corresponding control mode according to the judgment result, distributing the aerodynamic power or the thrust sub-target for each rotor, generating the rotor speed and the pitch angle instruction signal of each rotor;Rotor aerodynamic adjustment execution module, for independently adjusting the main shaft speed and blade pitch angle of each rotor according to the instruction signal. The present application effectively improves the aerodynamic coordination, power generation efficiency and structural safety of multi-rotor floating wind turbine under full working condition.

The application provides a motor state estimation method, a motor controller and an electric drive assembly, and relates to the technical field of motors.The motor state estimation method comprises the following steps: determining a current error according to a current observation value and a current feedback value of a motor, performing closed-loop control according to the current error to determine a back electromotive force deviation, and performing closed-loop control according to the back electromotive force deviation to determine a rotor speed and a position angle of the motor.Through the establishment of a current error feedback adjustment mechanism, the back electromotive force observation is more robust, the rotor speed and the angle are further controlled by using the back electromotive force deviation, the system state is indirectly deduced through the system output error, the closed-loop estimation mechanism is formed, the estimation value can be continuously corrected through the error negative feedback mechanism, the field orientation is more accurate, the high-speed control without a position sensor is realized, and the control performance, stability and dynamic response capability of the motor under high-speed or variable load conditions are improved.

This invention discloses a sensorless speed and displacement control method for a bearingless permanent magnet synchronous motor. The method involves acquiring the current and voltage components of the torque winding in a stationary coordinate system, processing them through a nonlinear flux linkage observer to obtain a rotor angle error signal, and then processing this error signal through an extended state observer phase-locked loop to obtain the rotor speed and angle. Based on the deviation between the rotor speed and the speed setpoint, a closed-loop speed adjustment is performed to generate a torque winding control signal. The method also involves acquiring the motor-side current component and the current and voltage components of the levitation winding in a rotating coordinate system, processing them through an effective flux linkage observer to obtain the rotor radial displacement component in the rotating coordinate system, and then transforming this displacement component based on the rotor angle to obtain the displacement in the stationary coordinate system. Based on the deviation between this displacement and the displacement setpoint, a closed-loop displacement adjustment is performed to generate a levitation winding control signal.

This disclosure provides an electric motor control apparatus and an image forming apparatus. The electric motor control apparatus detects the current flowing through the coils of each phase of the electric motor, estimates the rotational position of the motor rotor based on the detected current values, and in motor control that switches the excitation phase of the motor according to a target rotor speed, determines a current command value for the current component that generates torque in the rotor based on the phase difference between the command value and the estimated value of the rotational position. The electric motor control apparatus controls the current supplied to the coils of each phase of the motor according to the determined current command value.

This invention discloses a flywheel-battery hybrid energy storage method and system for suppressing grid power oscillations, relating to the field of power system stability control technology. It includes: acquiring the real-time rotor speed of the flywheel energy storage unit; generating a first power command based on the deviation from a preset rated speed; determining whether the real-time rotor speed is within a preset speed range; if it exceeds the limit, generating a second power command to control the battery energy storage unit to charge and discharge at a constant power; if it is within the range, generating a third power command based on the DC bus voltage deviation; and controlling the battery to execute the commands based on priority arbitration logic, with the second power command having higher priority than the third power command. This invention addresses the problems of existing centralized control architectures heavily relying on complex communication, experiencing response delays, and batteries suffering from shallow charging and discharging and rapidly declining lifespan due to frequent tracking of power oscillations.

The invention provides an adjusting device, method, system and equipment for adjusting states of three red lines of an engine, and relates to the field of airworthiness verification tests of the engine, the adjusting device comprises a swirler, the swirler is arranged in an air inlet channel of the engine, and the swirler is arranged perpendicular to the axis of the engine. The swirler comprises a swirl guide vane which can rotate in the radial direction of the engine, so that the pre-swirl angle of the swirler is adjustable. According to the invention, the thrust of the engine is effectively reduced by controlling the rotation of the rotational flow guide vane, adjusting the pre-rotation angle of the swirler and reducing the flow of the outer culvert airflow of the engine, so that the engine is prevented from generating excessive thrust, and the thrust of the engine does not exceed the red line state too much when the rotating speed of the rotor reaches the red line state; the strength and the service life of key components such as an engine fan, a gas compressor and a turbine are ensured.

The application discloses a kind of parameter identification-based speed regulation method and system, belong to motor parameter identification technical field, to solve the problem of conventional parameter online identification mechanism using fixed convergence gain, the problem of speed estimation oscillation instability caused by the departure from underlying thermodynamic law;Its method includes: using the law of conservation of thermodynamic energy to determine the highest possible physical change rate of motor stator temperature, set the physical speed limit boundary of parameter online identification mechanism, obtain dynamic convergence gain with physical boundary perception;Construct a sliding mode observer with adaptive identification interface, perform stator resistance parameter identification through the received dynamic convergence gain, and analyze the actual rotor speed of the synchronous motor through the obtained stator resistance identification value and adjust the output power of the circulating water pump.The application suppresses the oscillation instability phenomenon of stator resistance identification value, and guarantees the accuracy of synchronous motor speed analysis and the stability of circulating water pump output power under high temperature alternating conditions.

This application belongs to the field of aero-engines, and specifically relates to a control algorithm for aero-engines accelerating according to the rate of increase of engine speed. The algorithm includes: calculating the planned value of the high-pressure rotor speed change rate control based on the speed change rate control law and the current relative equivalent speed of the high-pressure rotor; calculating the maximum deviation of the high-pressure rotor speed change rate based on the speed change rate limit law and the current relative equivalent speed of the high-pressure rotor; calculating the speed change rate deviation based on the current speed change rate and the high-pressure rotor speed change rate control plan value, and taking the smaller value between the deviation and the maximum value to obtain the change in the high-pressure rotor speed change rate; interpolating the acceleration oil correction amount from the acceleration oil correction coefficient law; obtaining the current acceleration oil-air ratio and the compressor outlet total pressure, and calculating the planned value of the fuel flow rate during the acceleration process; obtaining the fuel flow rate limit value and taking the smaller value between the fuel flow rate limit and the planned value to obtain the final fuel flow rate.

The invention relates to a method for determining a rotational speed and a rotor positional angle in sensorless drives, preferably in a sensorless operation of a permanently excited synchronous machine, wherein the calculation is based on a first voltage error (Δ_ud_1′) and a second voltage error (Δ_ud_2′) from an angle variation in ud, and based on a first voltage error (Δ_uq_1′) and a second voltage error (Δ_uq_2′) from a rotor speed variation in uq. The invention also relates to a computer program and a a control device.

In permanent magnet rotary electric machines, the rotor speed can be increased compared to previous methods. Multiple magnetic flux barriers are formed on the rotor core. These magnetic flux barriers include outer and inner magnetic flux barriers. Both the outer and inner magnetic flux barriers are arched. Compared to the inner magnetic flux barrier, the outer magnetic flux barrier is a flattened arch. The circumferential ends of the outer magnetic flux barrier have a constricted shape where the slot width gradually narrows circumferentially outwards.

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 application belongs to the field of main fuel control, and particularly relates to a main fuel control method for preventing a turbofan engine from turning down, comprising the following steps: setting a slow-speed high-pressure rotor speed deviation value, obtaining a current high-pressure rotor speed in real time, comparing the current high-pressure rotor speed with the slow-speed high-pressure rotor speed set value to obtain a deviation between the current high-pressure rotor speed and the slow-speed high-pressure rotor speed set value; obtaining a current slow-speed high-pressure rotor speed deviation value, determining a corrected acceleration oil flow rate according to an acceleration oil correction amount; obtaining the corrected acceleration oil flow rate, controlling the engine to obtain a new slow-speed high-pressure rotor speed deviation value; judging whether the new slow-speed high-pressure rotor speed deviation value meets a rotor speed deviation threshold value, and if yes, exiting the main fuel control. The method can timely find a rotor speed abnormality decrease condition and identify a turning-down risk of the engine, and when the engine has the turning-down risk, the acceleration oil flow rate is corrected to ensure that the engine can sufficiently increase the oil supply amount and avoid the engine from turning down.

A method and controller for controlling an axial flux machine are described, wherein alternating current supplied to multiple coils is injected as a compensating current to reduce the mechanical resonance components of the rotor. This compensating current is added to an orthogonal current (IA) as the rotor rotates within one or more speed ranges. q ) component and DC (I d The modulated current component is a modulation current component of at least one of the following components (when the alternating current is represented as a vectorized DC component). This modulated current component has: an electrical frequency that varies with the rotor speed within a frequency range between a first frequency and a second frequency, including a frequency substantially the same as the rotor's fundamental mechanical resonant frequency; and a phase that is different from the rotor's fundamental mechanical resonant frequency.

The application discloses a kind of unmanned plane artificial wind field precision construction method and system based on rotor airflow regulation, belong to unmanned plane automatic control technical field.For solving existing unmanned plane rotor airflow random diffusion, it is difficult to accurately construct specific direction and form artificial wind field in target area, the method of the present application includes: setting target parameter of demand artificial wind field;Rotor airflow regulation strategy is generated based on target parameter, through the collaborative control of each rotor speed, phase and lift ratio, the downwash airflow is superimposed or interfered in the target area, while generating the attitude regulation strategy of three degrees of freedom control of the flow guide device below the unmanned plane, the downwash airflow is guided and shaped;Dynamic correction is carried out on the regulation strategy based on feedback information during operation to maintain the stability of the wind field.The present application realizes the active control of wind field form and action intensity, and can be used for crop pollination, fruit dew removal, precision spraying and crown layer microclimate regulation and other operations.