703 results about "Rotor speed" patented technology

An electronic starting switch assembly and control methods for a dryer having a split-phase induction motor. The assembly comprises a microcontroller unit (MCU) configured to execute a control method that dynamically manages the motor's operation by monitoring the forward magnitude current. The MCU determines a stabilized startup forward magnitude current and calculates a crossover condition, allowing for precise control of the motor's transition to single-phase operation by disconnecting the auxiliary winding and connecting the heater element based on real-time forward magnitude current analysis and processing. The system can also monitor for overload conditions indicative of rotor speed drops and can re-engage the auxiliary winding to maintain motor performance. The assembly includes a housing with a heat-sink for efficient thermal management and environmental protection of electronic components. The disclosed method provides a robust solution for efficient dryer operation by ensuring accurate control of motor start-up, running conditions, and overload protection.

The invention discloses an inertia support control method and system for a high-inertia energy storage type synchronous phase modifier, and the method comprises the steps: determining the frequency deviation of a power grid based on the frequency of the power grid when the voltage of the power grid is greater than or equal to a preset voltage threshold value, judging whether the frequency deviation exceeds a dead zone range or not, and obtaining a judgment result; when the judgment result indicates that the frequency deviation exceeds a dead zone range, disturbance, inertia support and primary frequency modulation function input of the system frequency occur, an active current instruction value is generated according to the frequency deviation, and the power grid frequency is controlled based on the active current instruction value; the rotor speed is obtained in real time, when the rotor speed reaches the rotor speed limit value, the active output instruction is set to be zero, the dead zone range is adjusted till the rotor speed is recovered to the preset range, the dead zone range is recovered to be normal, and the active output instruction is unlocked.

The invention discloses a rotor unbalance rapid adjustment method based on Kalman filtering, and belongs to the technical field of rotor dynamic balance. According to the method, a rotor rotating speed signal is obtained through a magnetic encoder, and a piezoelectric vibration sensor is triggered to collect a radial vibration signal. In the aspect of signal processing, a zero phase shift filter is adopted to remove noise interference, and an initial phase and an amplitude are extracted by using FFT (Fast Fourier Transform). And calculating a rotating speed change rate based on the sliding time window, and judging whether the rotor is in a steady-state or transient-state working condition. Under the transient working condition, a state space model containing amplitude, phase and rotating speed is constructed, and unbalance adjustment parameters are predicted through Kalman filtering recursion; and under a steady-state working condition, accurately calculating a correction parameter by adopting a least square method. In addition, a least square fitting model based on a sine function is constructed, amplitude estimation is optimized, and the unbalance calculation precision is improved. According to the invention, the unbalance of the rotor can be quickly and accurately adjusted, and the stability and the service life of a rotating system are improved.

The invention discloses a motor control method and device, electronic equipment and a storage medium. The method comprises the following steps: acquiring a three-phase current, converting the three-phase current into a total current of a current period in a static coordinate system, and extracting a high-frequency current of the current period from the total current; extracting a rotor position and a rotor rotating speed from the high-frequency current; compensating the rotor rotating speed by using the expected rotating speed to obtain a quadrature-axis expected current; converting the total current into a quadrature-direct axis coordinate system, extracting a fundamental frequency current from the quadrature-direct axis coordinate system, compensating the fundamental frequency current by using a quadrature axis expected current and a direct axis bias current to obtain a first expected voltage, superposing the first expected voltage and a direct axis high-frequency voltage, and performing coordinate system conversion on a superposition result by using a rotor position to obtain a second expected voltage; obtaining a second expected voltage under the static coordinate system; and the three-phase current of the current period is controlled according to the second expected voltage to drive the motor, so that the motor has more obvious salient polarity through the direct-axis bias current, and vector control over the electrode is achieved.

The invention relates to a coaxial multi-rotor unmanned aerial vehicle control method based on a Koopman operator, and the method comprises the steps: constructing a deep neural network based on the Koopman operator, and mapping a state variable to a high-dimensional observable space through an encoder; in a high-dimensional observable space, state variables are predicted through a linear connection layer based on dimension rising state variables and rotor rotating speeds; the decoder restores the prediction result to an original state space; training a deep neural network by using historical flight data to obtain codec parameters and a weight of a linear connection layer, and constructing a linear dynamic model of the observation function and the unmanned aerial vehicle; and the prediction controller predicts state variables of future multiple steps of the unmanned aerial vehicle by using a linear dynamics model, and enables the unmanned aerial vehicle to track a given trajectory by minimizing a cost function to obtain optimal control input. Compared with the prior art, the method has the advantages that complete data-driven modeling is realized, and the method can adapt to unmanned aerial vehicles with different sizes, loads and flight conditions.

One variation of a system for generating thrust at an aerial vehicle includes: a primary electric motor; a rotor coupled to the motor; an internal-combustion engine; a clutch interposed between the motor and an output shaft of the internal-combustion engine; an engine shroud defining a shroud inlet between the rotor and the internal-combustion engine, extending over the internal-combustion engine, and defining a shroud outlet opposite the rotor; a cooling fan coupled and configured to displace air through the engine shroud; and a local controller configured to receive a rotor speed command specifying a target rotor speed, adjust a throttle setpoint of the internal-combustion engine according to the target rotor speed and a state of charge of a battery in the aerial vehicle, and drive the primary electric motor to selectively output torque to the rotor and to regeneratively brake the rotor according to the target rotor speed.

The invention discloses a two-degree-of-freedom thrust vector dual-rotor flight control method and device. The method comprises the following steps: analyzing and designing a two-degree-of-freedom thrust vector dual-rotor structure; according to the two-degree-of-freedom thrust vector dual-rotor structure, deriving a two-degree-of-freedom thrust vector dual-rotor dynamic model; a control distribution equation is deduced according to the kinetic model of the two-degree-of-freedom thrust vector double rotors, the kinetic model is decomposed into a matrix combination form through the control distribution equation, and the rotation angle of a joint and the rotation speed of the rotors are solved through the control distribution equation; according to the dynamic model of the two-degree-of-freedom thrust vector dual-rotor, a pose cascade PID-ADRC controller is designed, and the pose cascade PID-ADRC controller comprises a position cascade PID-ADRC controller and an attitude cascade PID-ADRC controller. The method has good control and stabilization effects on the two-degree-of-freedom thrust vector double rotors.

The invention belongs to the technical field of aviation equipment industry, and particularly relates to an electric power inspection unmanned aerial vehicle which comprises an unmanned aerial vehicle body, a high-definition camera, a temperature sensing variable resistance plate, a flaming foreign matter removing mechanism, a load reduction feedback mechanism, a rotor rotating speed self-adjusting compensation mechanism, a lubricating state visual display mechanism and a PLC. The rotor speed of the unmanned aerial vehicle can be automatically adjusted based on the environment temperature and the condition that the load of the unmanned aerial vehicle is reduced due to fuel consumption in the use of the flaming mechanism, the flight stability of the unmanned aerial vehicle is ensured, and the situation that the unmanned aerial vehicle is more sensitive to airflow and wind direction changes due to excessive lift force can be avoided; according to the method, the problem that the flight stability is influenced due to the fact that the lubricating oil loss condition in the flight process of the unmanned aerial vehicle can be automatically calculated is solved, so that workers can arrange the maintenance time more reasonably, and unnecessary premature maintenance or too late maintenance is avoided.

The invention discloses a floating fan pool test model blade optimization design method and device based on an NSGA-III algorithm, a medium and a program. The method comprises the steps that firstly, the aerodynamic coefficient of a real fan blade airfoil and the Reynolds number of a floating fan model blade are calculated; selecting an appropriate low-Reynolds-number fan blade airfoil to replace a model blade airfoil and calculating an aerodynamic coefficient; calculating a target thrust value and a torque value of the floating fan model under different test required wind speeds; performing linear fitting to obtain a linear function of a lift coefficient linear region of the real type and the model blade relative to the attack angle; calculating the final chord length of the model blade; and finally, on the basis of an NSGA-III algorithm, the rotor rotating speed and the blade pitch angle of the floating fan model at different wind speeds are optimized by taking the minimum relative error of the thrust and the torque as a target. According to the invention, the thrust and torque of the model fan are matched with the target thrust and torque under different wind speed scales, the test accuracy is improved, and resources are saved.

The invention relates to a non-inductive FOC open-loop to closed-loop switching method and device for an electronic water pump and a vehicle. The method comprises the steps that a rotor is pre-positioned; starting an open loop I-F; switching condition judgment; estimating the rotor speed based on an observer, calculating a normalization factor, and obtaining a mixed scale factor through cubic polynomial operation; acquiring an open-loop current instruction of a q axis and a closed-loop current instruction output by a closed-loop speed PI regulator; performing weighted synthesis on the two paths of current instructions according to the mixing scale factor to obtain a temporary target current instruction, and applying a change rate limit to obtain a final current instruction output in the current period; the original angle error of the observer estimation angle and the open-loop slope angle is calculated and normalized, the allowable adjustment step length and direction of the round are dynamically determined, and the angle correction amount of the round is generated and superposed to the open-loop slope angle to update the rotor angle reference value; and closed-loop switching is completed. According to the invention, the problems of electromagnetic torque impact and rotating speed fluctuation caused by instruction step change are solved.

The invention relates to a dynamic and static pressure mixed gas radial bearing, and belongs to the technical field of air bearings. The shaft sleeve is sleeved with the bearing seat, a limiting part is arranged outside the shaft sleeve, and a limiting groove is correspondingly formed in the inner wall of the bearing seat; in the radial direction, the bump foil assemblies are arranged between the shaft sleeve and the bearing seat, and in the circumferential direction, the bump foil assemblies are arranged between the limiting parts at intervals; a plurality of first air inlet holes are formed in the bottom of the limiting groove, a plurality of second air inlet holes are formed in the limiting part, and the first air inlet holes correspond to the second air inlet holes in position. According to the design, the integrity of the bump foil assembly can be guaranteed, the structure is simple, machining is convenient, and mounting and dismounting are more convenient. When the speed of the rotor is low, the static pressure gas forms a gas film, and the bearing capacity of the dynamic and static pressure mixed gas radial bearing is enhanced. When the rotating speed of the rotor is high, dynamic pressure can be generated on the basis of static pressure, and the dynamic pressure and static pressure mixed gas radial bearing has larger bearing capacity due to superposition of the dynamic pressure and the static pressure.

A method and system to control a rotor system includes automatically changing a rotor speed of the rotor system of the tiltrotor aircraft while moving the rotor system from a first position and a first rotor speed to a second position and a second rotor speed over a time period in accordance with an acceleration-rate profile that varies over the time period using a controller communicably coupled to the rotor system of the tiltrotor aircraft.

The present invention discloses a method and system for calibrating the zero position of a permanent magnet synchronous motor with different rotation speeds, and relates to the technical field of drive motors for new energy electric vehicles. The method includes: S1: pre-positioning the rotor position and determining the initial zero position value of the resolver; S2: controlling the drive motor to a predetermined speed; S3: implementing zero current control through a controller to allow the motor speed to drop freely; S4: adjusting the zero position value of the resolver to keep the target voltage at zero; S5: recording the zero position value of the resolver at different speeds and fitting the curve to complete the calibration. According to the technical solution of the present application, high-precision resolver zero position angle calibration can be achieved without the need for additional bench resources, which reduces the complexity of the calibration process and has high practical value.

One variation of a system for generating thrust at an aerial vehicle includes: a primary electric motor; a rotor coupled to the motor; an internal-combustion engine; a disengagement mechanism interposed between the motor and an output shaft of the internal-combustion engine; an cooling shroud defining a shroud inlet between the rotor and the internal-combustion engine, extending over the internal-combustion engine, and defining a cooling shroud outlet opposite the rotor; a cooling fan coupled and configured to displace air through the cooling shroud; and a local controller configured to receive a rotor speed command specifying a target rotor speed, adjust a throttle setpoint of the internal-combustion engine according to the target rotor speed and a state of charge of a battery in the aerial vehicle, and drive the primary electric motor to selectively output torque to the rotor and to regeneratively brake the rotor according to the target rotor speed.

The disclosure relates to monitoring blades of a wind turbine rotor shaft. Example embodiments include a computer-implemented method of monitoring blades of a wind5 turbine (100), the wind turbine (100) having a plurality of blades (103a, 103b) mounted to a hub (102), each blade (103a) comprising one or more strain sensors (109a1-3) mounted to the blade (103a) at corresponding respective distances from the hub (102, 201) along the blade (103a), the method comprising: i) recording (1301) strain measurements from the strain sensors (109a1-3) on each of the plurality of blades10 (103a); ii) recording (1302) a rotor speed of the wind turbine (100); iii) calculating (1303) a statistical measure of each of the recorded strain measurements; iv) calculating (1304) a difference in the statistical measure for strain sensors at corresponding positions on each of the plurality of blades over a range of rotor speeds; and v) identifying (1305) the presence or absence of damage in one of the plurality of blades15 based on the calculated difference.

The invention discloses a flight control device, an aircraft control method and a vertical take-off and landing aircraft, and relates to the technical field of aircraft control. The first joystick is configured to receive manipulation information input by a pilot; the second joystick is configured to receive manipulation information input by a pilot; and the processor is configured to generate a vector control instruction by using a signal corresponding to the control information received from the first control rod and / or the second control rod and combining a preset control mapping relation, and control the aircraft to perform vector motion according to the vector control instruction. And when the vector control instruction is an aircraft course control instruction, controlling the aircraft to perform yawing motion at least through tilt angle differential control and / or rotor speed differential control and / or lifting rudder deflection. According to the scheme, the control complexity of the aircraft can be effectively reduced, and then the operation burden of a pilot is relieved.

The invention discloses a wind power plant equivalent virtual inertia identification method based on symbol regression, and relates to the technical field of novel power system frequency safety and stability, and the method comprises the steps: S1, building a doubly-fed fan inertia response dynamic mechanism model containing comprehensive inertia control; according to the method, the problems of lack of physical mechanisms, poor evaluation interpretability and the like of an equivalent virtual inertia evaluation method for a current wind power plant are solved, the method is based on system operation data and is associated with an inertia response dynamic mechanism model, and the interpretability of a system physical process is reserved; a sparse dynamic modeling method is adopted, an input-output linear combination feature library of system electromagnetic torque-rotor rotating speed change is constructed, sparse solution of parameters is achieved through a sequence threshold value least square algorithm, and the equivalent virtual inertia of the wind power plant is obtained through evaluation. According to the method, model priori knowledge and operation data are fully applied, and the evaluation result is high in accuracy and high in interpretability.

This disclosure pertains to the field of wind power technology and provides a method, system, equipment, and medium for calculating the velocity distribution of a wind turbine wake field. The method includes: acquiring wind speed, rotor speed, and airfoil aerodynamic data; constructing a prediction function for the wind turbine based on blade deformation data to output load distribution; inputting current blade deformation data to obtain the load distribution; calculating the blade spanwise circulation distribution based on relevant data; obtaining the intensity of wake vortices and shedding vortices based on the circulation distribution, thereby obtaining the wake control point position vector; and solving for the velocity distribution at any location within the downstream wake field of the wind turbine. This process aims to more accurately predict the relevant characteristics of the wind turbine wake field and solve the problem that existing wake field prediction models cannot consider the true shape of the wake. This method can consider the true shape of the wake to obtain an accurate wake field velocity distribution.

The invention belongs to the field of offshore wind power, and discloses a single-pile offshore wind turbine power regulation and load relief method, which comprises the following steps of: constructing a thrust system model of wind to a rotor and a tower; constructing a dual-mass transmission system model of the wind turbine generator; constructing a tower top front-back displacement model and a pile soil front-back displacement model; constructing a rotor speed tracking error model based on an adjustment error method; constructing a tracking error model of the change rate of the front-back displacement of the tower top; constructing an optimal control strategy based on an infinite vision field optimal cost function; and designing an optimal pitch control scheme based on a robust adaptive dynamic programming algorithm. According to the design of the RADP-based propeller pitch controller provided by the invention, the MOWT model does not need to be completely known, so that the calculation cost of the controller is reduced, and the calculation efficiency is improved.

The invention discloses a method, a system, a medium and equipment for evaluating a blade tip timing vibration displacement measurement error under a variable rotating speed. A blade end vibration displacement measurement value is generated based on an included angle between a blade end timing sensor and a rotating speed sensor, an included angle between a rotor blade root and a key phase reference on a rotating shaft, reference arrival time measured by a key phase sensor and a blade end rotating radius; a blade end timing vibration displacement measurement error mathematical model under the variable rotating speed is established, and a measurement error caused by the variable rotating speed is obtained based on the blade end vibration displacement measurement value; evaluating the maximum error of the blade tip timing vibration displacement measurement under the variable rotating speed, and obtaining the maximum error of the blade tip timing vibration displacement measurement under the variable rotating speed based on the measurement error; based on the measurement error and the blade end timing vibration displacement measurement maximum error under the variable rotation speed, the influence of the rotor rotation speed change speed and the blade initial angle position on the blade end timing vibration displacement measurement error is quantified.

The invention discloses a method for reducing the mechanical impact load of a steering system. The method comprises the steps that S1, the motor rotor acceleration torque Ta of the steering system is monitored and calculated in real time; s2, judging whether the acceleration torque Ta of the motor rotor meets a preset condition or not; if a preset condition is met, entering the step S3, otherwise, returning to the step S1; step S3, outputting a target torque request TRML; the value of the target torque request TRML is determined according to an expected minimum target level lambda for reducing the external impact load and an external impact load value; the direction of the target torque request TRML is the same as the direction of the motor rotor speed n. Impact damage of external impact loads to the steering system and an internal key part worm gear under the special driving working condition can be reduced, the service life of the worm gear is guaranteed and even prolonged, the reliability of the steering system is improved, and the noise vibration performance of the steering system and the hand feeling of a driver are improved.

The invention relates to a ship-borne unmanned aerial vehicle recycling method and system based on visual navigation and six-degree-of-freedom compensation. The method comprises the following steps: extracting infrared, polarization and fluorescence frequency domain features and fusing to obtain an anti-shielding composite descriptor; constructing a ship dynamics differential model, discretizing the ship dynamics differential model by adopting an explicit multi-step method, and predicting six-degree-of-freedom disturbance data of the ship; a vision and inertia combined cost function is constructed, a vision residual item is calculated, the continuity of the motion track of the unmanned aerial vehicle is restrained, and the optimized real-time pose of the unmanned aerial vehicle is obtained; decomposing the six-degree-of-freedom disturbance data into a body coordinate system compensation amount, setting a backstepping sliding mode control law containing feed-forward compensation, and generating an anti-disturbance trajectory instruction; and air data are collected in real time, the rotor rotating speed is corrected according to the air data, the electromagnetic adsorption force is calculated, and the ship-borne unmanned aerial vehicle is recycled. And the navigation stability under complex sea conditions is enhanced.

The invention discloses an aero-engine acceleration control method with an interstage combustion function. In the acceleration process, the fuel flow of the main combustion chamber and the fuel flow of the interstage combustion chamber are generated through the main control loop and the additional control loop correspondingly, and then the finally-output fuel flow of the main combustion chamber and the finally-output fuel flow of the interstage combustion chamber are obtained in a low selection mode. Adjusting each variable geometry adjusting mechanism according to an acceleration adjusting plan generated by the additional control loop; the additional control loop uses the following oil supply continuing control strategy that in the acceleration process, the main combustion chamber supplies oil to accelerate firstly, after the rotating speed of a low-pressure rotor of the engine reaches a preset threshold value, the interstage combustion chamber supplies oil to ignite, and meanwhile the variable geometry adjusting mechanism is adjusted according to a pre-optimized adjusting plan. The invention further discloses an aero-engine acceleration control device with the interstage combustion function. According to the technical scheme, safe and quick response of the double-combustion-chamber acceleration process can be achieved.

The invention discloses an unmanned aerial vehicle power system sensorless control temperature identification method, and belongs to the technical field of motor control. The method aims at solving the problem that temperature identification in a permanent magnet synchronous motor driving system of an unmanned aerial vehicle depends on rotor position information, and closed-loop coupling contradiction exists between the temperature identification and rotor position estimation needed by sensorless control. Comprising the following steps: establishing a permanent magnet synchronous motor complex vector model based on extended back electromotive force in an estimated synchronous rotation gamma-delta reference system; establishing a full-order state sliding mode observer based on a complex vector by taking the stator current and the extended counter electromotive force as state variables; performing forward Euler discretization to obtain a full-order state sliding mode observer in a discrete domain, and observing a stator current estimated value and an extended back electromotive force estimated value; obtaining a rotor observation position and a rotor observation rotating speed; and designing an affine projection algorithm, identifying the stator resistance in real time in combination with a segmented regularization factor strategy, and estimating based on the stator resistance obtained by identification to obtain a motor temperature estimation value. The method is used for motor temperature identification.

The invention provides an improved sliding-mode observer for permanent magnet synchronous motor position sensorless control. A traditional sliding-mode observer can cause a jitter phenomenon of observation information in motor control. According to the method, the control equation of the sliding-mode observer is redesigned, the adaptive rate is combined, and a low-pass filter is replaced, so that the estimation precision of the back electromotive force is improved. A hyperbolic tangent function is used to replace a sign function to alleviate the jitter problem of the observer, and a phase-locked loop technology is used to replace an arc tangent function to reduce estimation errors and phase delay. The feasibility of the control system is verified by building a system simulation model based on a static coordinate system in MATLAB / Simulink. A simulation result shows that the control system reduces the rotor speed error and the rotor position error, so that the control performance and the stability of the permanent magnet synchronous motor are improved.

The invention discloses a high-efficiency multifunctional rotor speed reducer assembling device and method. A rack comprises a rack body, a press-fitting platform and a press-fitting area, wherein the press-fitting platform and the press-fitting area are arranged on the rack body; the tray conveying mechanism is arranged on the press-fitting platform, a rotor press-fitting seat and a speed reducer press-fitting seat are arranged on the tray, and the tray conveying mechanism is used for conveying the rotor press-fitting seat and the speed reducer press-fitting seat to a press-fitting area; the back plate is arranged on the frame body through the back plate transplanting mechanism, and the back plate transplanting mechanism is used for driving the back plate to transversely slide relative to the frame body; the grabbing mechanism is arranged on the back plate, and the grabbing mechanism is used for grabbing the rotor; the pressing mechanism is arranged on the back plate and is used for pressing a main shaft bearing on the rotor; the tightening mechanism is arranged on the back plate and used for tightening a bearing end cover on the speed reducer; the rotating mechanism is located behind the grabbing mechanism, connected with the grabbing mechanism and used for rotating the rotor. All the mechanisms are accurate in positioning and coordinated in action, accurate matching of the rotor and the speed reducer is ensured, and assembly errors are reduced.

The invention particularly relates to a helicopter auxiliary landing visual system in a sand blowing environment. The system is composed of a helicopter main rotor, a rotor hub, a main rotor speed reducer, a camera protection cover, a pan-tilt camera, a camera lifting rod, a lifting rod fixing bolt, a motor, a speed reducer, a deep groove ball bearing and a helicopter body. According to the design, the pan-tilt camera and the lifting device are installed in the propeller hub of the main rotor, when the ground and the surrounding environment need to be monitored, the motor speed reducer drives the lead screw to rotate, the lifting rod drives the pan-tilt camera to extend to the position above the rotor by a certain distance, and at the moment, the pan-tilt camera can monitor wider and more comprehensive environment information. According to the system, when the helicopter flies, hovers or lands close to the ground in a dry environment containing a large number of dispersed phase particles such as sand, adverse effects caused by the particles such as the sand can be effectively reduced, and the flight safety is improved.

A circuit for automatically calculating a speed of a rotor includes: an edge generation module configured to receive Hall signals of three phases, and generate an edge response signal for the Hall signal of each phase; a counting module, which is connected to an output end of the edge generation module, configured to count the time difference between two adjacent jumps of the Hall signal of each phase on the basis of an output signal of the edge generation module to obtain a count value of each phase, output the current count value, and generate a trigger signal when the Hall signal of any phase jumps; and a division module, which is connected to an output terminal of the counting module, configured to divide an angle difference between the two adjacent jumps of the Hall signal by the current count value to obtain a rotation speed of an electric motor.

The invention relates to the technical field of aero-engine aerodynamic optimization and computer aided design, and discloses a response surface modeling-based aero-engine low-pressure turbine blade leading edge model numerical optimization design method and structure. According to the method, the wake injection angle is changed by adjusting the flow or the rotating speed of a rotor, accurate matching of Klebanoff stripes and large-scale vortex generation opportunities is achieved, stripe impact is promoted, and large-scale vortex fracture is accelerated; and meanwhile, by constructing a blade front edge modeling parameterization model and establishing a response surface agent model of a modeling design variable parameter combination and a boundary layer velocity mean square error, an optimal design variable parameter combination is determined in a constraint domain by taking maximization of the velocity mean square error in a boundary layer as a target. On the premise that the blade profile load is not changed, the momentum thickness and the total pressure loss of the boundary layer are effectively reduced, the design efficiency and the engineering applicability under the working condition of the low Reynolds number are improved, an additional flow control structure does not need to be introduced, and the structure is simple and easy to implement.

The invention relates to the technical field of unmanned aerial vehicle control, in particular to a physical-data hybrid fault diagnosis method and system for an electric vertical take-off and landing aircraft. The method comprises the following steps: firstly, selecting a proper flight state variable to construct an observer, and generating a residual signal between a rotor rotating speed estimation value and a tracking value; secondly, introducing a random forest to realize positioning isolation of rotor faults; a data set is constructed by integrating physical model data, a random forest classification model is trained, a physical-data hybrid diagnosis model is established, dynamic association between flight states and faults is captured, and multi-fault diagnosis of eVTOL under closed-loop control is realized.