79 results about "Icing conditions" patented technology

The invention discloses a data-mechanism fused airport runway surface water and ice condition prediction method. The method comprises the following steps: establishing a theoretical model of a runway surface temperature field and a water and ice condition; thermal parameter inversion is carried out on the theoretical model based on actually measured data, and a dynamic theoretical model adapted to an actual application scene is obtained through multi-time iteration optimization of model parameters; and utilizing the fused time sequence data and the dynamic theoretical model to predict the water and ice condition on the surface of the airport runway, and providing dynamic evolution information of the icing process. According to the method, the problems of insufficient real-time performance and accuracy of runway icing prediction in the prior art are solved, the icing time, the ice layer thickness and the ice layer range of the runway surface can be accurately predicted, real-time deicing decision support is provided, and the runway operation safety and the airport operation efficiency are effectively improved.

The invention relates to the technical field of fan monitoring, and discloses a fan blade icing monitoring method and system, computer equipment, a medium and a product, the method comprises the following steps: collecting multi-source data, the multi-source data comprising data of a plurality of sensors arranged at preset positions of a fan blade, environmental meteorological data and fan operation data; fusing the multi-source data, and performing feature extraction on the fused data to obtain a comprehensive feature vector; monitoring the icing condition of the current fan blade based on the comprehensive feature vector and a preset deep learning model to obtain icing condition information; and performing early warning on the icing state of the fan blade based on the size relationship between the icing condition information and a preset threshold value. Through organic combination of multiple advanced technical means such as multi-source data fusion, deep learning, icing condition information prediction and early warning of the icing state of the fan blade, the problem of low accuracy of icing monitoring of the fan blade in a complex environment in the prior art is effectively solved.

The invention discloses an iced conductor galloping amplitude prediction method and system and a storage medium, and belongs to the technical field of power system safety monitoring and prediction.The method comprises the steps that environmental meteorological data of a power transmission conductor are collected in real time and preprocessed; inputting the preprocessed environmental meteorological data into a pre-constructed conductor dynamic response prediction model under the normal working condition to obtain a galloping amplitude prediction value of the transmission conductor under the normal working condition; inputting the preprocessed environmental meteorological data into a pre-constructed icing thickness prediction model to obtain an icing thickness prediction value; determining a lift coefficient and a resistance coefficient based on the preprocessed wind speed data and the icing thickness prediction value; and calculating an equivalent aerodynamic coefficient according to the lift coefficient and the resistance coefficient, converting the galloping amplitude predicted value of the transmission conductor under the normal working condition in combination with a pre-constructed nonlinear conversion formula, obtaining the galloping amplitude predicted value of the transmission conductor under the current icing condition, and transmitting the galloping amplitude predicted value to a monitoring center in real time.

The invention discloses a wing icing full-period sensing and early warning method, and belongs to the field of aircraft icing detection and early warning. The method comprises the following steps: firstly, acquiring cloud particle data, flight parameter sensing data and planar electrode icing detection data; then, the cloud particle data and the flight parameter data are preprocessed, and the impact efficiency of the cloud particles impacting the surface of the wing and the icing mass flow rate are obtained; and finally, constructing a mixed model based on a BP neural network and a recurrent neural network, and processing the time sequence data through a long-short-term memory unit to realize prediction of the icing condition. According to the invention, a multi-scale dynamic cloud field in real flight can be monitored, the ice thickness and the ice type of predicted icing can be output in real time, and at the same time, multi-stage early warning thresholds are set to realize gradient early warning output of potential risk prompts; the icing prediction result correction in the real-time flight process can be realized, and the prediction accuracy is improved; the method has the advantages of high-precision prediction, real-time monitoring, strong generalization and the like, and is suitable for icing safety protection under complex meteorological conditions.

The present invention relates to the field of detection equipment technology, solving the technical problem in the prior art that sensors are still easily lost in severe icing conditions. In particular, it relates to an anti-icing sensor with a V-shaped concave-convex groove on the windward side. A temperature measuring end is provided on the side of the sensor housing away from the mounting seat. The temperature measuring end is provided with an anti-icing structure. The sensitive element is connected to the sensor housing and is located on the inner side or leeward side of the temperature measuring end. The cross-section of the windward end parallel to the airflow direction is an isosceles triangle. The first vertex of the isosceles triangle of the windward end faces the direction of the incoming flow. The groove at the front edge of the windward end has a V-shaped cross-section. As the flow direction extends, the groove width increases with a linear gradient and the groove depth decreases with a linear gradient, forming a continuous three-dimensional topological surface. The present invention uses the different affinity and repellency surface properties of the concave-convex steps to break up water droplets and even water films, accelerate the flow of water droplets in the groove, reduce the overall ice adhesion of the windward end surface by nearly half, and greatly reduce the damage of ice to downstream components.

The invention provides a low-energy-consumption mechanical anti-icing and de-icing device and method and an aircraft skin structure, and the device comprises a passive anti-icing part which comprises an elastic interlayer, and the elastic interlayer is used for being adhered to the first side face of a skin of an aircraft; the elastic interlayer at least comprises a lubricating material capable of reducing the ice adhesion strength; the active deicing part comprises a force applying device, and the force applying device faces the second side face, away from the first side face, of the skin; wherein the aircraft is frozen to form an ice layer-elastic interlayer-skin three-layer structure under the freezing condition, the force application device applies stress load to the second side face of the skin, and the ice layer is actively induced to be broken; through deformation of the elastic interlayer, stress load is concentrated on the ice layer, critical fracture displacement needed for inducing fracture of the ice layer is passively reduced, and meanwhile, through the anti-adhesion effect of the elastic interlayer, the fractured ice layer is promoted to fall off from the elastic interlayer. Through the device provided by the invention, efficient deicing with low energy consumption, repeated use and no damage to the skin structure is realized.

The invention discloses an optimization method for preventing freezing in cold start of a fuel cell, and relates to the technical field of fuel cells, the optimization method comprises the following steps: S1, collecting environment temperature and stack internal freezing condition data, and analyzing water production rate and temperature rise ice melting capability; s2, constructing a prediction model capable of reflecting the relationship among the environment temperature, the internal icing condition of the electric pile and the ideal current density; s3, inputting the environment temperature and the internal icing condition of the electric pile into the prediction model, and adjusting the parameters of the fuel cell; the air temperature is indirectly controlled through a current density curve predicted by a model, stack water production-ice melting balance is converted into a flow distribution optimization problem, and voltage fluctuation feed-forward compensation is combined, so that cooperative control of the temperature and the electrochemical state is realized, the performance of the fuel cell in the cold start process is optimized, and the performance of the fuel cell in the cold start process is improved. And the stability and the output efficiency of the system are enhanced, and powerful technical support is provided for application of the fuel cell in a low-temperature environment.

The invention discloses an ice-coated blade aeroelastic flutter and complete machine mistuning identification method based on multi-dimensional dynamic feature engineering, and belongs to the technical field of wind power. Comprising the steps of collecting original multivariable time series data, preprocessing the original multivariable time series data, performing feature extraction on the preprocessed original multivariable time series data from three dimensions of time domain, time-frequency domain wavelet energy and control system domain to obtain basic physical features, performing feature screening on the basic physical features based on a Gini index, and obtaining the basic physical features. The method comprises the following steps: obtaining a fault seed feature, constructing an interactive feature and an adaptive feature based on the fault seed feature, fusing the basic physical feature, the interactive feature and the adaptive feature into a high-dimensional feature set, and inputting the high-dimensional feature set into a weighted ensemble learning classifier to realize the identification of the ice-coated blade health, aeroelastic flutter and complete machine detuning state. According to the method, the problems of poor fault identification robustness and low precision of a traditional method are solved, and reliable guarantee is provided for safe and stable operation of the wind turbine generator under the icing working condition.

The invention discloses a power transmission line icing monitoring algorithm based on fiber grating sensor data fusion. The algorithm comprises the steps of sensor data acquisition and dynamic preprocessing, icing mechanical model establishment, icing load solving, icing thickness iterative solving and anomaly detection and fault tolerance. According to the method, the icing density and the wind load coefficient are dynamically corrected through multi-dimensional data fusion of tension, inclination angle, wind speed, temperature and humidity, the icing thickness is iteratively calculated by adopting a Newton-Rafson method, and adaptive processing of abnormal working conditions is realized in combination with abnormal data detection and historical mean rollback. According to the invention, the precision and stability of icing detection can be effectively improved, the line icing condition can be accurately evaluated in real time in a complex meteorological environment, and the accident risk and the operation and maintenance cost are reduced.

The invention provides an airfoil icing ice shape rapid prediction method based on empirical wavelet transform. The airfoil icing ice shape rapid prediction method comprises the steps of obtaining icing meteorological parameters; the icing meteorological parameters are input into a pre-trained target neural network, the empirical wavelet transform boundary value of the icing thickness curve signal and the first K-order Fourier modals of the icing thickness curve signal under the airfoil icing condition are predicted, and K is a positive integer; constructing a band-pass filter according to the empirical wavelet transform boundary value of the icing thickness curve signal under the airfoil icing condition; according to the band-pass filter and the front K-order Fourier mode of the icing thickness curve signal, obtaining each-order empirical wavelet transform mode; the empirical wavelet transformation modes of all orders are superposed, and an icing thickness curve signal is obtained; and performing target transformation on the icing thickness curve signal to obtain an airfoil icing ice shape. By implementing the method and the device, relatively high prediction accuracy can be kept under different conditions, the generalization ability of prediction is enhanced, and meanwhile, the prediction efficiency is improved.

The embodiment of the application provides a kind of fan blade anti-icing and deicing system and control method, control device and controller, for the control method of fan blade anti-icing and deicing system, comprising: obtaining the air temperature, air humidity and wind speed of the environment where fan blade is located;First icing thickness of the top of the nacelle of fan and the second icing thickness of the outer surface of fan blade are obtained;According to air temperature, air humidity and wind speed, the environmental urgency of fan blade is determined;And according to environmental urgency, first icing thickness and second icing thickness, the working mode of anti-icing and deicing system is controlled.The embodiment of the application can accurately control whether anti-icing and deicing system is started and works in anti-icing mode, ice melting mode or deicing mode according to different weather conditions and icing conditions of fan blade, avoid refusal to act and / or misoperation phenomenon due to equipment failure and / or monitoring principle, improve reliability and working efficiency, and ensure the stable operation of wind turbine generator during icing period.

An angle-adjustable component icing measurement and runoff water collection device belongs to the technical field of icing and anti-icing research on ships and marine structures. This invention solves the problem in existing droplet icing measurement devices where the height and angle of the component under test cannot be adjusted, thus failing to cover most components on the ship's superstructure surface for icing testing. The component under test is mounted on the top of a lifting support via an angle adjustment component, and its height is adjusted via the lifting support. A limiting element is inserted into corresponding limiting through holes and blind holes to achieve circumferential limiting between two limiting cylinders, with the component under test fixed to the second limiting cylinder. This allows for changes in the angle and height of the component under test, enabling the acquisition of icing conditions at different windward positions on the ship's superstructure. It overcomes the limitation of traditional icing devices that can only simulate flow from a single direction, avoids the need for multiple component replacements, and effectively improves experimental efficiency.

The invention provides an aircraft deicing operation device and method. The device comprises a ground preheating and filling module; the vehicle-mounted deicing operation module comprises an electric chassis, a pressure-bearing heat preservation liquid tank, a spraying unit and a vehicle-mounted inert gas power unit. The high-pressure nitrogen source is communicated with the liquid tank through the pressure adjusting unit and provides spraying driving force for liquid in the tank. The spraying unit selectively communicates with the liquid tank for liquid spraying or communicates with the gas power unit for nitrogen purging. The method comprises the steps that the ground module is used for centralized heating and filling; in the deicing standby period, the liquid temperature is maintained through the heat preservation liquid tank; the high-pressure nitrogen source is started during operation, and a continuous injection mode and a pulse injection mode are selected according to ice conditions; during operation, the pressure is maintained to be stable by adjusting the pressure compensation liquid level change. According to the preheating and vehicle-mounted heat-source-free driving device, the safety of deicing operation of an airplane is improved.

This application presents a state assessment method for the stability of the bow-net current collection quality under icing conditions. First, a test platform for the stability of the bow-net current collection quality under icing conditions is built. Based on the built test platform, the parameters of the bow-net current collection quality stability under icing conditions are measured by various sensors. Based on the parameters measured by the sensors, the average bow-net offline rate ρ and the speed performance factor P are calculated. v , contact resistance stability factor H r , pantograph-catenary current stability factor G under icing conditions w Finally, the stability of the pantograph-catenary current collection quality under icing is assessed. The present invention can more accurately assess the stability of the pantograph-catenary current collection quality under icing, allowing timely measures to de-ice and melt the iced catenary, thus ensuring safe railway operation.

This invention provides a fast prediction method for airfoil icing shape based on empirical wavelet transform, comprising: acquiring icing meteorological parameters; inputting the icing meteorological parameters into a pre-trained target neural network to predict the empirical wavelet transform boundary values ​​of the icing thickness curve signal under airfoil icing conditions and the first K order Fourier modes of the icing thickness curve signal, where K is a positive integer; constructing a bandpass filter based on the empirical wavelet transform boundary values ​​of the icing thickness curve signal under airfoil icing conditions; obtaining empirical wavelet transform modes of each order based on the bandpass filter and the first K order Fourier modes of the icing thickness curve signal; superimposing the empirical wavelet transform modes of each order to obtain the icing thickness curve signal; and performing a target transform on the icing thickness curve signal to obtain the airfoil icing shape. By implementing this invention, high prediction accuracy can be maintained under different conditions, the prediction generalization ability is enhanced, and the prediction efficiency is improved.

The invention provides an icing warning information output method. The icing warning information output method comprises the following steps: step 1, initializing icing state information; 2, the icing detector circularly detects the icing thickness according to a preset period, whether the icing strength at the current moment is in a non-icing state or not is judged according to the icing thickness at the current moment, and if yes, the step 4 is executed; if not, skipping to the step 3; thirdly, the freezing speed is calculated according to the freezing thickness corresponding to the current moment and the freezing thickness corresponding to the previous moment; 4, outputting the icing alarm information at the current moment according to the icing thickness at the current moment and the icing alarm information at the previous moment; 5, the icing detector circularly receives the deicing control instruction according to a preset period, and the deicing operation is triggered according to the deicing control instruction at the current moment; and 6, returning to the step 2. The icing condition of the aircraft can be visually and efficiently presented for a pilot, the icing risk is effectively warned, and the icing vigilance is improved.

The present invention provides a method for reducing test ice shape errors, comprising conducting n repetitive icing wind tunnel tests under the same test model and icing conditions; placing n sets of acquired three-dimensional test ice shape point cloud data in the same data space under the same position reference conditions, thereby overlapping the n sets of point cloud data; projecting the overlapped point cloud data onto a two-dimensional plane along the model height direction to obtain two-dimensional overlapping point cloud data; clustering the data to obtain a two-dimensional average ice shape; calculating a tolerance band for the two-dimensional average ice shape; using the two-dimensional average ice shape and its tolerance band combination to quantitatively describe the target ice shape; and performing regression interpolation on characteristic points on the ice shape curve to obtain a smooth parameterized ice shape curve that filters out noise points on the numerical ice shape curve. The present invention can reduce the error of three-dimensional test ice shape and improve the accuracy of icing wind tunnel tests, with lower cost, simpler operation, clearer theory, greater practicality, and more significant results.

According to the wind turbine generator blade icing dynamic early warning system provided by the invention, through omnibearing monitoring of the frequency modulation continuous wave radar group, the orthogonal weaving piezoelectric fiber array and the infrared temperature measurement unit, airspace water drop distribution, blade vibration characteristics and multi-dimensional dynamic changes of a surface temperature field are accurately captured; by combining improved Kalman filtering, wavelet transformation and a dynamic weight distribution algorithm of an intelligent decision module, traditional single threshold judgment is upgraded to comprehensive threat index deduction based on digital twinborn bodies, and the temporal-spatial resolution and reliability of icing threat assessment are remarkably improved; the execution control module achieves heating network partition accurate regulation and control and unit operation state collaborative optimization according to the generated anti-icing strategy, energy waste of traditional global heating is avoided, material damage caused by local overheating or underheating is effectively restrained, finally, anti-icing energy consumption is reduced under the complex meteorological condition, and the anti-icing efficiency is improved. And meanwhile, the power generation efficiency loss of the unit under the icing working condition is greatly reduced.

The present application relates to the technical field of deicing robot, and more particularly to a multi-split intelligent flying conductor deicing robot, which comprises a main body, a flying arm, a deicing execution assembly, a posture adjusting assembly and a control assembly. The present application synchronously collects multi-dimensional state parameters, identifies the envelope state according to the spatial mapping relationship of configuration and adhesion, calculates the consistency index of multi-station operation through the distribution dispersion of contact length and the cooperativity of vibration response, analyzes the deviation of walking load in different conductor directions, and jointly diagnoses the efficiency mismatch type. Then, according to the state type and the imbalance source, the contact compensation, configuration adjustment or collaborative balance strategy is dynamically matched and directional linkage adjustment is carried out. Finally, the convergence trend of the adjusted parameters is verified, effectively solving the problem of slow response speed and low deicing efficiency in the face of complex and variable icing conditions due to the dependence on fixed mechanical deicing mode.

The invention discloses an ice crystal icing test device and test method for an aero-engine. The ice crystal icing test device comprises a radiation heating device and a controller. And the radiation heating device is arranged at the upstream of the test piece in the conveying direction of the airflow. And the radiation heating device comprises a cylindrical outer cover and a radiation heater arranged on the inner surface of the cylindrical outer cover. And the inner cavity of the cylindrical outer cover is hollow, so that air flow reaches the test piece through the inner cavity. The airflow contains ice crystals, and the ice crystals are radiated and heated by the radiation heater in the inner cavity to be heated. And the controller is electrically connected with the radiant heater to control the work of the radiant heater. The ice crystal icing test device provided by the embodiment of the invention can simulate ice crystal icing conditions of an aero-engine more truly.

The embodiment of the disclosure provides an automatic activation control method of an intelligent anti-icing and snow-removing control system, comprising: dividing an anti-icing and snow-removing heating area based on real-time temperature and icing condition data of an aircraft surface; activating a heating device of a corresponding area when detecting that a specific area has an icing risk; dynamically adjusting the power of each heating area according to environmental conditions and flight states; recording and analyzing the working state of each heating area, and optimizing future partition strategies to improve the energy efficiency ratio. Through the scheme of the embodiment of the disclosure, the problem of how to intelligently partition the heating area to balance the energy consumption and the anti-icing efficiency can be solved.

Embodiments of the present disclosure provide systems and methods for averting, shedding, or otherwise managing ice accretions that may develop during flight of an aircraft. Example systems and methods generate heat at targeted areas of a propeller assembly by electric heating systems that utilize propeller motion.

METHOD AND CONTROL UNIT FOR CONTROLLING THE CLEARANCE OF A HIGH-PRESSURE TURBINE TO REDUCE THE IMPACT OF ICING. Method for controlling the clearance between the blade tips of an aircraft engine turbine rotor and a turbine ring, comprising estimating a nominal clearance to be controlled and controlling a valve delivering an airflow directed to the turbine ring as a function of the nominal clearance thus estimated, method wherein, to prevent the formation of ice that could affect the aircraft engine, the estimated nominal clearance is increased if the on / off result of a predetermined control logic indicates that icing conditions are present and until conditions for returning to normal operation are present, the predetermined control logic being a function of the following parameters: ambient temperature, altitude, temperature T12, and rotational speed of a low-pressure shaft. Figure for abstract: Fig. 3.

The present invention provides a method and system for icing warning of low-altitude aircraft based on meteorological observation. The method includes obtaining historical meteorological data, historical flight data, aircraft own data and icing conditions of the low-altitude aircraft in the same period; respectively establishing corresponding neural network models according to the division of icing components, and respectively training them to obtain corresponding target neural network models; obtaining various data collected by the low-altitude aircraft in real time, respectively inputting them into the corresponding target neural network models, and outputting corresponding icing thickness and icing type; judging whether the preset icing components reach the warning standard according to the output results of the target neural network models; if so, giving a first warning; if not, performing weighted processing according to the icing thickness and icing type of each icing component to obtain an evaluation value; judging whether the evaluation value is greater than a threshold; if so, giving a second warning. Specifically, by evaluating the icing situation of the aircraft, the flight risk can be effectively reduced.

The present application provides a method for controlling the on / off operation of an aircraft engine anti-icing system, the method comprising: determining a critical flight altitude based on specified icing conditions; determining the aircraft's flight Mach number based on the engine operating state being at the maximum inlet Mach number, the engine inlet airflow static temperature being at the icing temperature, and the ambient temperature being at the limit temperature, wherein the aircraft's flight Mach number is the critical flight Mach number; determining the anti-icing system's critical activation temperature based on an anti-icing heat demand formula; activating the anti-icing system when the aircraft's flight altitude, flight Mach number, and engine inlet total temperature are all less than the corresponding critical flight altitude, critical flight Mach number, and anti-icing system's critical activation temperature; and deactivating the anti-icing system when these conditions are less than the corresponding critical flight altitude, critical flight Mach number, and anti-icing system's critical activation temperature. The method provided in the present application, based on flight altitude signals, flight Mach number signals, and engine inlet total temperature signals, provides active anti-icing during the anti-icing system's on / off operation, offering greater safety than passive anti-icing performed after icing using an ice detector.

This invention provides a method and system for testing icing under rotating conditions of supercooled large water droplets, relating to the field of aero-engine icing testing. It aims to address the problem of excessive liquid water content caused by significant settling of supercooled large water droplets and the inability of the uniform cloud zone to cover the test specimen. The method includes: obtaining the projected area S of the rotating test specimen on the test cross-section under rotating conditions. A ; Obtain the overlapping area S of the cloud and fog region between the uniform cloud and fog region and the projected area of ​​the rotating test specimen. B The liquid water content obtained from the calibration test is L. B According to the projected area S A Area S where clouds and fog overlap B and liquid water content of L B The liquid water content L corresponding to the freezing condition of the rotating test piece was obtained. A By using the relative area of ​​the uniform cloud and fog zone and the test zone, liquid water is equivalently transformed. The freezing condition conversion method of the rotating state test under the freezing condition of supercooled large water droplets is adopted, which effectively supports the rotating state test under the freezing condition of supercooled large water droplets.

The present application relates to the field of power equipment performance detection, and discloses a device and method for detecting the service life of power lines under extremely cold conditions in remote mountainous areas, comprising an extreme temperature environment simulation unit, an icing simulation unit, a mechanical vibration unit, an observation and comparison unit and a control unit; at least two independent and symmetrical test cabins are formed in the insulation box for simultaneously accommodating power line samples from different manufacturers; the control unit is electrically connected with the extreme temperature environment simulation unit, the icing simulation unit, the mechanical vibration unit and the observation and comparison unit, used for adjusting the start and stop of the compression refrigerating machine of the extreme temperature environment simulation unit to maintain the temperature in the test cabin within a preset extremely cold temperature range, controlling the icing simulation unit to spray water mist into the test cabin to simulate icing conditions, controlling the rotational speed of the mechanical vibration unit to adjust the vibration frequency and amplitude of the power line sample, and comprehensively evaluating the service life of the power line sample based on the data collected by the observation and comparison unit.

The application relates to the technical field of fan monitoring, and discloses a fan blade icing monitoring method, a system, computer equipment, a medium and a product, the method comprising the following steps: collecting multi-source data, the multi-source data comprising data of multiple sensors arranged at preset positions of fan blades, environmental meteorological data and fan operation data; fusing the multi-source data, and performing feature extraction on the fused data to obtain a comprehensive feature vector; monitoring the current fan blade icing condition based on the comprehensive feature vector and a preset deep learning model to obtain icing condition information; and warning the fan blade icing state based on the size relationship between the icing condition information and a preset threshold. The application effectively solves the problem of low accuracy of fan blade icing monitoring in complex environments in the prior art by organically combining various advanced technical means such as multi-source data fusion, deep learning, icing condition information prediction and warning of the fan blade icing state.

The present application relates to the technical field of icing detection, and relates to an aircraft icing detection method and apparatus, and an aircraft. In the method, datasets at different time points and total air temperature data are acquired, and the datasets are compared to detect changes in the external environment of the aircraft or within the fields of view of windshields. If visible moisture is detected and the total air temperature is lower than a preset threshold, it is determined that an icing condition is satisfied. The present application can reduce the pilot's workload in icing determination, thereby improving flight safety.

The application provides a two-dimensional airfoil critical ice shape determination method, device and equipment and a storage medium, relates to the airfoil icing data processing technical field, and the method can more accurately describe the critical influence of the airfoil aerodynamic performance by determining the evaluation parameter corresponding to each icing condition in the current population, performs genetic operation on the current population to obtain a new current population, and determines the evaluation parameter corresponding to each icing condition in the current population again, determines a target icing condition based on the maximum value of the evaluation parameters corresponding to all icing conditions, and determines a two-dimensional airfoil critical ice shape based on the ice shape characteristic parameter corresponding to the target icing condition. By using the evaluation parameter and the genetic algorithm, the global optimal critical ice shape can be automatically found in the entire continuous flow field parameter set space, the locality and blindness of the manual point selection method are overcome, and the efficiency and accuracy of the critical ice shape determination can be improved.