54 results about "Icing conditions" patented technology

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 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 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 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.

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 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.

The invention discloses a pneumatic thermal composite anti-icing and deicing device and a control method thereof, and relates to the technical field of plasmas, the pneumatic thermal composite anti-icing and deicing device comprises a composite heating film, the composite heating film comprises an insulating substrate layer, a functional heating layer, a lower electrode array, an upper electrode array and a surface protection layer, and the pneumatic thermal composite anti-icing and deicing device further comprises an airborne anti-icing and deicing power supply; and a plasma jet disturbance assembly is arranged at an easy-to-freeze area at the front edge of the device component. The functional heating layer provides stable and uniform substrate heating, and ensures that the whole protective surface is maintained in a non-icing temperature range; under the extreme icing condition, the composite working mechanism shows obvious advantages. The electrothermal film is responsible for melting an ice-film interface and reducing the adhesion strength; and the plasma-induced ion wind provides continuous pneumatic shear force to promote the overall stripping of the ice layer.

The invention relates to a method, a device and equipment for generating an anti-galloping strategy of an icing contact network, and a medium. The generation method comprises the following steps: acquiring contact network information, and constructing a first hydrodynamic simulation model of the contact network under an icing condition according to the contact network information and preset icing information; according to preset wind power information, carrying out aerodynamic characteristic analysis on the first fluid mechanics simulation model to obtain a first aerodynamic coefficient; according to the preset galloping information, the preset wind power information and the first aerodynamic coefficient, carrying out galloping instability analysis on the icing contact network to obtain a first galloping coefficient; constructing a second fluid mechanics simulation model according to the configuration information of the anti-galloping device, wherein the anti-galloping device is integrated on the contact network; performing aerodynamic and galloping analysis on the second fluid mechanics simulation model according to preset wind power information and preset galloping information to obtain a second aerodynamic coefficient and a second galloping coefficient; and according to the aerodynamic coefficient and the galloping coefficient, generating an anti-galloping strategy capable of efficiently inhibiting vertical galloping of the overhead line system.

The present invention discloses an air data probe integrated with an inverted single helix heater cable for controlling one or more icing parameters. The air data probe comprises a hollow structure and one or more grooves. The hollow structure is designed such that it is exposed to fluid during flight, allowing for interaction with one or more icing parameters. The one or more grooves provide a path for an electrical heater cable. The electrical heater cable, featuring an underside bend for efficient heat distribution is integrated into the one or more grooves. The inverted single helix heater cable significantly elevates performance during icing conditions by maintaining optimal temperatures at critical areas prone to icing.

The invention relates to test benches for pieces of aviation equipment and can be used for testing an engine and propeller assembly (an engine with a propeller mounted thereto) for small unmanned aerial vehicles under icing conditions. A test bench for testing an engine and propeller assembly for ice accretion comprises a freezing chamber, a system for supplying power to and controlling the revolutions of the engine and propeller assembly undergoing testing, a system for monitoring the state of the engine and propeller assembly undergoing testing, meters for measuring the air temperature and humidity inside the freezing chamber, a two-phase nozzle for spraying water onto the engine and propeller assembly undergoing testing, and systems for supplying water and compressed air to the two-phase nozzle, wherein, in addition to a compressor with a tank, a pipeline, a filter and a compressed air pressure regulator, the system for supplying compressed air comprises an air dryer. The technical result of the invention is that of providing more accurate test results using a compact and energy efficient test bench.

A pneumatic-performance-quality integrated monitoring method for an aircraft under the condition of cumulus icing comprises the following steps: acquiring geometric parameters, flight state parameters and environmental parameters of the aircraft, then sequentially calculating a pneumatic flow field and icing parameters of a clean aircraft configuration, performing surface equivalent roughness mapping, and obtaining a result obtained by pneumatic recalculation after icing; and then flight performance and flight quality evaluation is performed according to a result obtained by aerodynamic recalculation after icing, when a flight performance evaluation result or a flight quality evaluation result exceeds a preset safety threshold range, a flight control strategy is triggered, and compensation control is performed on the aircraft by adjusting engine thrust, a control surface deflection angle or flight control parameters, so that the flight quality is improved. Therefore, the aerodynamic stability and the flight safety of the aircraft under the icing condition are maintained. According to the method, the calculation complexity caused by traditional ice shape geometric reconstruction and re-division can be reduced, the flight parameter acquisition efficiency after icing is improved, and the flight state monitoring of the aircraft in the cumulus icing state is efficiently realized.

This invention discloses a safety distance early warning system and method for OPGW lines in icing areas, specifically relating to the field of power system line operation monitoring technology. The system includes the following steps: status acquisition, spatial modeling, distance calculation, dynamic comparison, and trend prediction. By acquiring meteorological parameters in real time, a position function of the conductor and optical cable in space is constructed, the minimum spatial distance is calculated, and compared with a dynamic distance threshold to identify the risk level. Historical data and a difference evolution algorithm are combined to predict the distance change trend, triggering an early warning in advance, thus achieving dynamic assessment and proactive intervention control of distance risks under icing conditions. This invention achieves accurate dynamic monitoring, real-time risk assessment, and trend early warning of the minimum spatial distance between the fiber-optic composite overhead ground wire and the conductor in icing areas. It possesses the beneficial effects of comprehensive data acquisition, accurate modeling and calculation, timely risk identification, and proactive early warning intervention, significantly improving the safety and responsiveness of line operation.

The application discloses a polar ship icing condition limit stability evaluation method and system, and the method comprises the following steps: obtaining ship data and environmental parameters, inputting a dynamic icing calculation model, and calculating the ship icing distribution; obtaining the ship stability righting lever curve according to the real-time motion state of the ship and the ship icing distribution, processing the ship stability righting lever curve, and obtaining the dynamic stability curve; calculating the limit dynamic inclination and the maximum dynamic inclination lever under different icing conditions based on the dynamic stability curve, and solving the limit wind speed and the wind scale that can be borne by the ship under different icing conditions according to the calculation results, and comprehensively evaluating and judging the limit stability of the polar ship. The application realizes the dynamic update of the icing distribution with the change of the ship motion state by obtaining the state change parameters corresponding to the ship at each time step based on the six-degree-of-freedom motion equation of the ship, and the total amount of flying spray is calculated by combining the sea wave spray and the wind-generated flying spray, so that the ship stability analysis combines the icing and the wind wave, and the accuracy and the reliability of the stability evaluation are improved.

This invention proposes a method for monitoring early icing of aircraft based on ultrasonic pulse echo. The input parameters of this method include echo signals from ice-free structures, echo signals from iced structures, and the surface temperature of the structures. By analyzing and processing these input signals using the proposed method for early icing warning and ice thickness measurement based on ultrasonic pulse echo, early icing warning information and surface ice thickness data can be obtained, providing a basis for the activation and deactivation of the aircraft icing protection system. This invention can reduce the energy consumption of the aircraft icing protection system when removing ice from the aircraft surface, improving energy efficiency while ensuring flight safety, and has promising application prospects.

The application relates to a distributed electric heating icing protection system and relates to the technical field of electric heating deicing of an airplane, and comprises a surface coating layer covering the surface of the airplane skin, an electric heating layer and a detection layer below the surface coating layer; wherein the electric heating layer and the detection layer are arranged in layers, and are both distributed one-to-one unit structures; the heating components of the electric heating layer of each unit are uniformly arranged; the detection layer of each unit is provided with a detection element for detecting the icing condition; and the electric heating layer and the detection layer of each unit structure are independently controlled by a controller. Compared with the prior art, the uniformity of heat emission can be improved, and the deicing effect is better.

The invention provides a thyristor control method for an aircraft electric pulse deicing device, relates to the technical field of thyristor control and regulation, and aims to acquire and fuse multi-dimensional working condition data such as icing thickness, icing rate, environment temperature, environment humidity and flight data in real time, and calculate attitude influence factors to realize the control of the aircraft electric pulse deicing device according to the real-time attack angle and roll angle change of the aircraft. The icing aggravation trend of different pneumatic surfaces is predicted, the comprehensive icing severity index ISI is calculated for real-time quantitative evaluation, the deicing action can be automatically triggered in the early stage or the middle stage of ice condition development according to the icing speed, the low predefined interval, the middle predefined interval and the high predefined interval are judged according to the value of the ISI, and the deicing effect is improved. Compared with the prior art, the method has the advantages that deicing strategies with different emergency degrees are directly mapped, a time window from icing risk identification to effective deicing intervention application is shortened through a dynamic pre-judgment and hierarchical response mechanism, the coping capacity for sudden strong icing working conditions is improved, and the flight safety risk caused by untimely deicing is effectively reduced.

This application provides a method, apparatus, and aircraft for detecting aircraft icing, relating to the field of icing detection technology. The method includes: acquiring a first dataset and a second dataset at a first time point, and simultaneously acquiring total temperature data at the second time point; comparing the second dataset with the first dataset to detect changes in the aircraft's external environment or windshield field of view; if the changes in the aircraft's external environment and windshield field of view indicate visible moisture, and the total temperature data is below a preset threshold, then it is determined that the changes in the aircraft's external environment and windshield field of view meet a first icing condition. This application can reduce the workload of pilots in icing judgment and further improve flight safety performance.