Aircraft digital twin situation deduction and risk assessment method in complex meteorological environment

Abstract

The invention provides an aircraft digital twinning situation deduction and risk assessment method in a complex meteorological environment, and belongs to the technical field of data processing, the aircraft digital twinning situation deduction and risk assessment method in the complex meteorological environment comprises the following steps: collecting and processing weather data covering parameters such as wind direction and wind speed; obtaining aircraft performance parameters and building a database; and inputting and analyzing the flight plan. By establishing a three-dimensional deduction model including dynamics, weather influence and environment models, aircraft situations under different weathers are deduced, and flight safety, performance and task risks are evaluated. The method has the advantages that weather factors are comprehensively and accurately analyzed, and influences are quantified through data acquisition and processing and a meteorological model; the system is suitable for various aircrafts, can integrate navigation and control systems, and realizes remote monitoring management; risk assessment is scientific and reliable, multiple factors are integrated, powerful support is provided for flight decision making, and aircraft safety and task success rate in complex weather are effectively improved.

Description

Technical Field

[0001] The present invention belongs to the field of data processing technology, and specifically relates to a method for potential deduction and risk assessment of digital twins of aircraft in a complex meteorological environment. Background Art

[0002] For a long time, in flight demonstrations of traditional aircraft, flight trajectories were drawn using two- and three-dimensional grids. This expression method is not only not intuitive enough, but also limits the real-time constraints on the aircraft and is out of touch with the requirements of modern flight mission systems.

[0003] With the continuous development of aerospace technology, the flight safety of aircraft has received more and more attention. Weather conditions are one of the important factors affecting the flight safety of aircraft. Bad weather such as strong winds, heavy rains, and lightning may have an adverse effect on the performance and flight trajectory of aircraft, and even lead to flight accidents. Therefore, accurately predicting the impact of weather on aircraft, and conducting situation simulation and risk assessment are of great significance to ensuring the flight safety of aircraft.

[0004] At present, there are some methods for situational deduction and risk assessment of aircraft, but most of these methods do not fully consider the impact of weather factors, or simply use weather data as input parameters, lacking in-depth analysis and modeling of weather impacts. In addition, existing methods still have certain limitations in situational deduction and risk assessment in three-dimensional space, making it difficult to meet the needs of practical applications. Summary of the invention

[0005] The purpose of the present invention is to provide a method for digital twin situation deduction and risk assessment of aircraft in complex meteorological environments, aiming to solve the problem that the aircraft situation deduction and risk assessment technology in the prior art is insufficient in considering weather factors, it is difficult to accurately predict the situation and risks of aircraft in complex weather, and cannot meet the growing demand for flight safety.

[0006] To achieve the above object, the present invention provides the following technical solutions: A method for potential simulation and risk assessment of digital twins of aircraft in complex meteorological environments includes the following steps: S1. Weather data collection and processing: using meteorological equipment to collect real-time weather data, pre-processing the data and using meteorological models for analysis and prediction; S2, aircraft performance parameter acquisition, collecting the weight, size, aerodynamic characteristics and engine performance parameters of the aircraft and establishing a database; S3, flight plan input and analysis, input the flight plan of the aircraft and convert it into a flight trajectory; S4. Establish a three-dimensional aircraft situation deduction model based on the collected weather data, aircraft parameters and flight plan; S5. Use the established three-dimensional aircraft situation deduction model to deduce the flight situation of the aircraft under different weather conditions; S6. Based on the simulation results, assess the risk of the aircraft under different weather conditions; S7. Output the situation simulation results and risk assessment report of the aircraft under different weather conditions.

[0007] As a preferred solution of the present invention, the weather data includes wind direction angle parameters, wind speed parameters, temperature parameters, air pressure parameters and humidity parameters.

[0008] As a preferred solution of the present invention, the meteorological model includes the calculation of the effect of wind direction on the lateral force of the aircraft and the calculation of the effect of temperature on air density, which are specifically as follows:

[0009] ,

[0010] Where: is the lateral force, is the lateral force coefficient, is the air density, is the aircraft speed, is the frontal area of ​​the aircraft, is the wind direction angle;

[0011] ,

[0012] Where: is the air density, is the air pressure, is the gas constant, For the temperature.

[0013] As a preferred solution of the present invention, the three-dimensional aircraft situation deduction model includes an aircraft dynamics model, a weather impact model and a flight environment model. The aircraft dynamics model is used to describe the motion state and force conditions of the aircraft; the weather impact model is used to describe the impact of weather conditions on the aircraft; and the flight environment model is used to describe the flight environment in which the aircraft is located.

[0014] As a preferred solution of the present invention, the risk assessment includes flight safety risk assessment, flight performance risk assessment and flight mission risk assessment, wherein the flight safety risk assessment is calculated as follows:

[0015] ,

[0016] In the formula, For flight safety risks, is the probability of aircraft component failure, is the impact coefficient of the fault on flight safety.

[0017] As a preferred solution of the present invention, the flight safety risk assessment is used to assess the flight safety risk of an aircraft under different weather conditions; the flight performance risk assessment is used to assess the flight performance risk of an aircraft under different weather conditions; and the flight mission risk assessment is used to assess the flight mission risk of an aircraft under different weather conditions.

[0018] As a preferred solution of the present invention, the preprocessing in step S1 includes removing noise and outliers to improve the accuracy and reliability of data.

[0019] As a preferred solution of the present invention, the aircraft is one of an airplane, a helicopter or a drone.

[0020] As a preferred solution of the present invention, the method is integrated with the navigation system, control system, etc. of the aircraft to provide real-time decision support for the safe flight of the aircraft. The method realizes remote monitoring and management through the Internet, satellite communications, etc.

[0021] As a preferred solution of the present invention, the early warning signal can be in the form of sound and light alarm and text message notification.

[0022] Compared with the prior art, the present invention has the following beneficial effects:

[0023] 1. The present invention can comprehensively and accurately analyze weather factors, and conduct detailed data collection and processing, collect various weather data including wind direction angle, wind speed, temperature, air pressure and humidity, and pre-process the data to remove noise and outliers, improve the accuracy and reliability of the data, and use meteorological models containing specific calculation methods to conduct in-depth analysis and quantification of weather factors. Through these formulas, the impact of weather factors on the force and flight performance of the aircraft can be accurately calculated, providing a solid foundation for subsequent situation deduction and risk assessment;

[0024] 2. The present invention is applicable to various aircraft types such as airplanes, helicopters or drones. Whether it is a large civil airliner or a small drone, the technology can be used to conduct risk assessment before flight and situation deduction during flight to improve flight safety. This makes the technology have a wide range of application prospects and can meet the flight safety requirements of different types of aircraft under complex weather conditions. It can be integrated with the navigation system and control system of the aircraft and can achieve remote monitoring and management through the Internet, satellite communications and other means. When the risk assessment result exceeds the safety threshold, timely measures such as adjusting the flight plan, changing the flight altitude or speed can be taken to ensure flight safety.

[0025] 3. The present invention adopts a reasonable calculation formula and comprehensively considers multiple factors to make the evaluation results more scientific and reliable. The flight performance risk assessment considers the impact of weather conditions on aircraft performance, such as the impact of wind speed on aircraft speed, the impact of temperature on engine performance, etc.; the flight mission risk assessment comprehensively considers the flight plan and actual flight conditions to evaluate whether the aircraft can complete the flight according to the predetermined mission requirements; these risk assessments can comprehensively evaluate the risk situation of the aircraft under different weather conditions. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] The accompanying drawings are used to provide a further understanding of the present invention and constitute a part of the specification. Together with the embodiments of the present invention, they are used to explain the present invention and do not constitute a limitation of the present invention. In the accompanying drawings:

[0027] Figure 1 It is a flowchart of the present invention. DETAILED DESCRIPTION

[0028] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0029] Example 1

[0030] See also Figure 1 , the present invention provides the following technical solutions:

[0031] S1: Weather data collection and processing

[0032] Collection method: Use meteorological equipment to obtain real-time weather data;

[0033] Data processing: pre-process the collected data, including removing noise and outliers, and then use meteorological models for analysis and prediction; weather data covers parameters such as wind direction, wind speed, temperature, air pressure and humidity;

[0034] S2: Acquisition of aircraft performance parameters

[0035] Parameter collection: Collect the weight, size, aerodynamic characteristics and engine performance parameters of the aircraft and build a database; these parameters are crucial for subsequent model building and analysis;

[0036] S3: Flight plan input and analysis

[0037] Input content: Enter the flight plan of the aircraft, such as take-off location, destination, flight altitude, speed, etc.

[0038] Processing results: Convert the flight plan into a flight trajectory to provide a basis for subsequent situational deduction;

[0039] S4: Establish a 3D aircraft situation simulation model

[0040] Model composition: including aircraft dynamics model, weather impact model and flight environment model; aircraft dynamics model describes the motion state and force conditions of the aircraft; weather impact model describes the impact of weather conditions on the aircraft; flight environment model presents the environment in which the aircraft is located;

[0041] S5: Situational Simulation

[0042] Simulation basis: Based on the established three-dimensional aircraft situation simulation model, combined with weather data, aircraft parameters and flight plan, the flight situation of the aircraft under different weather conditions is simulated;

[0043] S6: Risk Assessment

[0044] Assessment types: including flight safety risk assessment, flight performance risk assessment and flight mission risk assessment; risk assessments are conducted on the safety, performance and mission completion of the aircraft under different weather conditions;

[0045] S7: Output results

[0046] Output content: Output the situation simulation results and risk assessment reports of the aircraft under different weather conditions. These results can be presented in the form of charts, text, etc. to provide support for flight decisions.

[0047] Specifically, the weather data includes wind direction angle parameters, wind speed parameters, temperature parameters, air pressure parameters and humidity parameters.

[0048] Specifically, the meteorological model includes the calculation of the effect of wind direction on the lateral force of the aircraft and the calculation of the effect of temperature on air density, as follows:

[0049] ,

[0050] Where: is the lateral force, is the lateral force coefficient, is the air density, is the aircraft speed, is the frontal area of ​​the aircraft, is the wind direction angle;

[0051] ,

[0052] Where: is the air density, is the air pressure, is the gas constant, For the temperature.

[0053] Specifically, the three-dimensional aircraft situation simulation model includes an aircraft dynamics model, a weather impact model and a flight environment model. The aircraft dynamics model is used to describe the motion state and force conditions of the aircraft; the weather impact model is used to describe the impact of weather conditions on the aircraft; and the flight environment model is used to describe the flight environment in which the aircraft is located.

[0054] Specifically, the risk assessment includes flight safety risk assessment, flight performance risk assessment and flight mission risk assessment, wherein the flight safety risk assessment is calculated as follows:

[0055] ,

[0056] In the formula, For flight safety risks, is the probability of aircraft component failure, is the impact coefficient of the fault on flight safety.

[0057] Specifically, the flight safety risk assessment is used to assess the flight safety risk of an aircraft under different weather conditions; the flight performance risk assessment is used to assess the flight performance risk of an aircraft under different weather conditions; and the flight mission risk assessment is used to assess the flight mission risk of an aircraft under different weather conditions.

[0058] Specifically, the preprocessing in step S1 includes removing noise and outliers to improve the accuracy and reliability of data.

[0059] Specifically, the aircraft is an airplane, a helicopter or a drone.

[0060] Specifically, the method is integrated with the navigation system, control system, etc. of the aircraft to provide real-time decision support for the safe flight of the aircraft. The method realizes remote monitoring and management through the Internet, satellite communications, etc.

[0061] Specifically, the early warning signal can be in the form of sound and light alarm and text message notification.

[0062] In a specific embodiment of the present invention, meteorological equipment such as meteorological satellites and meteorological radars are used to collect real-time weather data, including wind direction angle parameters, wind speed parameters, temperature parameters, air pressure parameters, and humidity parameters. These data are the basis for subsequent analysis and prediction. The collected data is processed to remove noise and outliers to improve the accuracy and reliability of the data. For example, high-frequency noise in meteorological data is removed by filtering algorithms, and obviously unreasonable outliers are identified and eliminated to ensure the quality of data input into subsequent models. Meteorological model analysis and prediction: A meteorological model containing a specific calculation method is used for analysis and prediction, wherein the formula Calculate the effect of temperature on air density. Accurate calculation of air density is crucial for analyzing the stress of the aircraft. At the same time, through the formula Calculate the impact of wind direction on the lateral force of the aircraft, which helps to accurately understand the force state of the aircraft in the wind and provide key data support for subsequent situation simulation and risk assessment;

[0063] Acquisition of aircraft performance parameters, parameter collection scope: Collect the weight, size, aerodynamic characteristics and engine performance parameters of the aircraft and establish a database. For example, the weight of the aircraft affects its flight inertia and fuel consumption; size parameters such as wing area are related to the calculation of lift and drag; aerodynamic characteristics include the shape coefficient of the wing, which determines the force of the aircraft in the air; engine performance parameters such as thrust and fuel efficiency directly affect the flight performance of the aircraft; establishing a database facilitates the management and query of the aircraft's performance parameters, and provides accurate aircraft characteristic data for the subsequent establishment of a three-dimensional aircraft situation deduction model;

[0064] Flight plan input and analysis, input content: input the flight plan of the aircraft, including the take-off location, destination, flight altitude, speed and other information. This information determines the flight path and expected flight status of the aircraft; convert the flight plan into a flight trajectory, which provides a reference path for the deduction of the aircraft's flight status in three-dimensional space, and facilitates the subsequent analysis of the deviation between the actual flight trajectory of the aircraft and the expected trajectory in combination with weather factors;

[0065] A three-dimensional aircraft situation deduction model is established, including an aircraft dynamics model, a weather impact model and a flight environment model. The aircraft dynamics model describes the aircraft's motion state and force conditions, including factors such as the aircraft's own weight, engine thrust, and aerodynamic force. Through precise mechanical analysis, it can simulate the aircraft's flight attitude and trajectory changes under different conditions. The weather impact model is used to describe the impact of weather conditions on the aircraft. It is based on collected and processed weather data, such as wind direction, wind speed, temperature, air pressure and humidity, and accurately calculates the impact of weather factors on the aircraft's force and flight performance, quantifies weather factors and integrates them into the aircraft's flight analysis. The flight environment model is used to describe the aircraft's flight environment, including factors such as the terrain and electromagnetic environment of the airspace, such as considering the impact of mountainous terrain on airflow and the impact of electromagnetic interference on the aircraft's communication and navigation systems. By integrating these three models, the three-dimensional flight situation of the aircraft under the influence of weather can be comprehensively and accurately deduced in a comprehensive framework.

[0066] Situation simulation uses the established three-dimensional aircraft situation simulation model, combined with the collected weather data, aircraft parameters and flight plan, to simulate the flight situation of the aircraft under different weather conditions. For example, consider the changes in the aircraft's flight trajectory under different wind directions and wind speeds, as well as the impact of temperature and air pressure changes on aircraft performance, so as to obtain the changes in the aircraft's actual flight attitude, speed, altitude and other parameters under various weather scenarios; the simulation results can be used to evaluate whether the aircraft can complete the flight mission as expected under different weather conditions, and predict possible flight risks;

[0067] Risk assessment includes flight safety risk assessment, flight performance risk assessment and flight mission risk assessment. Flight safety risk assessment is based on the formula The calculation refers to the probability of failure of aircraft components and the coefficient of influence of failure on flight safety. For example, if the probability of failure of aircraft engine components is high and the failure has a serious impact on flight safety, the flight safety risk will increase accordingly. The flight performance risk assessment considers the impact of weather conditions on aircraft performance, such as the impact of wind speed on aircraft speed and the impact of temperature on engine performance, and evaluates whether the aircraft can meet the flight performance requirements under different weather conditions. The flight mission risk assessment comprehensively considers the flight plan and actual flight conditions, and evaluates whether the aircraft can complete the flight according to the predetermined mission requirements, such as whether it can arrive at the destination on time, whether it can fly within the specified altitude and speed range, etc. Risk assessment can provide decision support for pilots and ground commanders by evaluating different types of risks, helping them decide whether they need to adjust the flight plan, take additional safety measures, or maintain and inspect the aircraft.

[0068] Output results, output the aircraft's situation simulation results and risk assessment reports under different weather conditions. These results can be presented in the form of charts, text, etc. For example, by drawing the aircraft's flight trajectory diagram under different wind directions and wind speeds, the changes in the aircraft's flight situation can be intuitively displayed; at the same time, the assessment results of the aircraft's flight safety risks, flight performance risks and flight mission risks are detailed in the form of a text report; the output results provide decision support for pilots and ground command personnel, helping them make reasonable flight decisions and ensure the safe flight of the aircraft.

[0069] This embodiment describes in detail the application of digital twin potential deduction and risk assessment technology for aircraft in complex meteorological environments in aircraft flight, demonstrates the functional role of various technical features and how they work together, and provides effective technical means to improve the safety and reliability of aircraft in complex weather conditions. Through accurate weather data collection and processing, comprehensive aircraft performance parameter acquisition, reasonable flight plan input and analysis, accurate three-dimensional aircraft situation deduction model establishment, detailed situation deduction, comprehensive risk assessment and effective result output, this technology can provide reliable decision support for the safe flight of aircraft.

[0070] Example 2

[0071] This implementation 2 provides a specific implementation method of a method for digital twin potential simulation and risk assessment of an aircraft in a complex meteorological environment. An aircraft is used as an example to illustrate the method. Weather data and aircraft performance parameters are obtained at the same time. The details are as follows:

[0072] Weather data collection and processing:

[0073] Collect real-time weather data, wind direction angle is 30°, wind speed is 20m / s, temperature is 25℃, air pressure is 1013hPa, and humidity is 60%;

[0074] Calculate air density: According to the formula , R is 287J / (kg·K), , ,but ;

[0075] Calculating lateral forces: Aircraft frontal area , lateral force coefficient ,

[0076] According to the formula ,but

[0077] ;

[0078] Aircraft performance parameter acquisition: collect aircraft weight, size, aerodynamic characteristics and engine performance parameters and establish a database;

[0079] Flight plan input and analysis: input the aircraft's flight plan and convert it into a flight trajectory;

[0080] Establish a three-dimensional aircraft situation deduction model: Based on the collected weather data, aircraft parameters and flight plan, establish a three-dimensional aircraft situation deduction model including aircraft dynamics model, weather impact model and flight environment model;

[0081] Conduct situation simulation: Use the established three-dimensional aircraft situation simulation model to simulate the flight situation of the aircraft under different weather conditions;

[0082] Conduct risk assessment: flight safety risk assessment, aircraft component failure probability , the impact coefficient of failure on flight safety , according to the formula ,but ;

[0083] Flight performance risk assessment and flight mission risk assessment: assessment is conducted based on simulation results and relevant parameters.

[0084] Output results: Output the situation simulation results and risk assessment reports of the aircraft under different weather conditions;

[0085] A risk assessment model is established, which comprehensively considers factors such as flight altitude, flight speed, weather conditions, and aircraft performance. Based on the situation simulation results, the risk probability faced by the aircraft at different flight stages is calculated, and the risks are graded so that pilots and ground commanders can take appropriate measures in a timely manner. When the risk assessment result exceeds the set threshold, an early warning signal is issued to remind pilots and ground commanders, and decision support suggestions are provided, such as adjusting the flight altitude, changing the flight speed, changing the route, etc., to reduce flight risks.

[0086] Example 3

[0087] This implementation 3 provides a specific implementation method of a method for digital twin potential simulation and risk assessment of an aircraft in a complex meteorological environment. A helicopter is used as an example to illustrate the method. Weather data and aircraft performance parameters are obtained at the same time. The details are as follows:

[0088] Weather data collection and processing:

[0089] Collect real-time weather data, wind direction angle is 120°, wind speed is 15m / s, temperature is 15℃, air pressure is 1000hPa, and humidity is 50%;

[0090] Calculate air density: According to the formula , R is 287J / (kg·K), , , ;

[0091] Calculating lateral forces: Aircraft frontal area Lateral force coefficient ,

[0092] According to the formula ,but

[0093] ;

[0094] Aircraft performance parameter acquisition: collect the helicopter's weight, size, aerodynamic characteristics and engine performance parameters and establish a database;

[0095] Flight plan input and analysis: input the helicopter's flight plan and convert it into a flight trajectory;

[0096] Establish a three-dimensional aircraft situation deduction model: Based on the collected weather data, aircraft parameters and flight plan, establish a three-dimensional aircraft situation deduction model including aircraft dynamics model, weather impact model and flight environment model;

[0097] Conduct situation simulation: Use the established three-dimensional aircraft situation simulation model to simulate the flight situation of the helicopter under different weather conditions;

[0098] Conduct risk assessment: flight safety risk assessment, probability of aircraft component failure , the impact coefficient of failure on flight safety , according to the formula ,but ;

[0099] Flight performance risk assessment and flight mission risk assessment: assessment is conducted based on simulation results and relevant parameters.

[0100] Output results: Output the situation simulation results and risk assessment reports of helicopters under different weather conditions;

[0101] A risk assessment model is established, which comprehensively considers factors such as flight altitude, flight speed, weather conditions, and aircraft performance. Based on the situation simulation results, the risk probability faced by the aircraft at different flight stages is calculated, and the risks are graded so that pilots and ground commanders can take appropriate measures in a timely manner. When the risk assessment result exceeds the set threshold, an early warning signal is issued to remind pilots and ground commanders, and decision support suggestions are provided, such as adjusting the flight altitude, changing the flight speed, changing the route, etc., to reduce flight risks.

[0102] Example 4

[0103] This implementation 4 provides a specific implementation method of a method for digital twin potential deduction and risk assessment of an aircraft in a complex meteorological environment. Taking a drone as an example, weather data and aircraft performance parameters are obtained at the same time. The details are as follows:

[0104] Weather data collection and processing:

[0105] Collect real-time weather data, wind direction angle is 60°, wind speed is 10m / s, temperature is 20℃, air pressure is 950hPa, and humidity is 40%;

[0106] Calculate air density: According to the formula , R is 287J / (kg·K), , ,but ;

[0107] Calculating lateral forces: Aircraft frontal area , lateral force coefficient ,

[0108] According to the formula ,but

[0109] ;

[0110] Aircraft performance parameter acquisition: collect the weight, size, aerodynamic characteristics and engine performance parameters of the UAV and establish a database;

[0111] Flight plan input and analysis: input the flight plan of the drone and convert it into a flight trajectory;

[0112] Establish a three-dimensional aircraft situation deduction model: Based on the collected weather data, aircraft parameters and flight plan, establish a three-dimensional aircraft situation deduction model including aircraft dynamics model, weather impact model and flight environment model;

[0113] Conduct situation simulation: Use the established three-dimensional aircraft situation simulation model to simulate the flight situation of the UAV under different weather conditions;

[0114] Conduct risk assessment: flight safety risk assessment, aircraft component failure probability , the impact coefficient of failure on flight safety , according to the formula ,but ;

[0115] Flight performance risk assessment and flight mission risk assessment: assessment is conducted based on simulation results and relevant parameters.

[0116] Output results: Output the situation simulation results and risk assessment reports of UAVs under different weather conditions;

[0117] A risk assessment model is established, which comprehensively considers factors such as flight altitude, flight speed, weather conditions, and aircraft performance. Based on the situation simulation results, the risk probability faced by the aircraft at different flight stages is calculated, and the risks are graded so that pilots and ground commanders can take appropriate measures in a timely manner. When the risk assessment result exceeds the set threshold, an early warning signal is issued to remind pilots and ground commanders, and decision support suggestions are provided, such as adjusting the flight altitude, changing the flight speed, changing the route, etc., to reduce flight risks.

[0118] The technology in the present invention breaks through the limitation of insufficient consideration of weather factors in traditional aircraft situation deduction and risk assessment; it not only collects various weather data such as wind direction, wind speed, temperature, air pressure and humidity, but also conducts in-depth analysis and quantification of weather factors through special meteorological models (such as formulas for calculating the influence of wind direction on lateral force and the influence of temperature on air density), providing a solid foundation for accurate situation deduction and risk assessment; different from the traditional two-dimensional and three-dimensional grid flight trajectory drawing method, a three-dimensional aircraft situation deduction model including aircraft dynamics model, weather impact model and flight environment model is established; it can comprehensively and accurately simulate the motion state, force condition and flight trajectory change of the aircraft under the influence of weather in three-dimensional space, which is more in line with the needs of modern flight mission systems; it is suitable for various aircraft types such as airplanes, helicopters or drones, and has broad application prospects; whether it is a large civil airliner or a small drone, this technology can be used for pre-flight risk assessment and situation deduction during flight to improve flight safety; it can be integrated with the navigation system and control system of the aircraft, and remote control can be achieved through the Internet, satellite communications, etc. Monitoring and management; It can provide pilots and ground commanders with the situation simulation results and risk assessment reports (including flight safety risk, flight performance risk and flight mission risk assessment) of aircraft under different weather conditions in real time, and present them in the form of charts, text, etc., to provide strong support for flight decision-making; for example, when the risk assessment results exceed the safety threshold, timely measures such as adjusting the flight plan, changing the flight altitude or speed can be taken to ensure flight safety; pre-processing is performed during the weather data collection process to remove noise and outliers and improve data accuracy and reliability; at the same time, the aircraft performance parameters are comprehensively collected and a database is established to provide accurate input for model calculation; in risk assessment, reasonable calculation formulas (such as flight safety risk assessment formulas) are used to comprehensively consider multiple factors to make the assessment results more scientific and reliable; although the model verification process is not mentioned in detail in the document, it can be inferred that during the technology development process, the model was verified and optimized through a large amount of experimental data and actual flight cases to ensure that the model can accurately reflect the actual situation of the aircraft under the influence of weather, thereby improving the reliability and practicality of the technology;

[0119] In summary, the digital twin potential simulation and risk assessment method of aircraft in complex meteorological environments has significant advantages in innovation, practicality and reliability, and provides an effective technical solution for improving the flight safety and mission success rate of aircraft in complex weather conditions.

[0120] Finally, it should be noted that the above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art can still modify the technical solutions described in the aforementioned embodiments or replace some of the technical features therein by equivalents. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A method for potential simulation and risk assessment of digital twins of aircraft in complex meteorological environments, characterized by: The steps include: S1. Weather data collection and processing: using meteorological equipment to collect real-time weather data, pre-processing the data and using meteorological models for analysis and prediction; S2, aircraft performance parameter acquisition, collecting the weight, size, aerodynamic characteristics and engine performance parameters of the aircraft and establishing a database; S3, flight plan input and analysis, input the flight plan of the aircraft and convert it into a flight trajectory; S4. Establish a three-dimensional aircraft situation deduction model based on the collected weather data, aircraft parameters and flight plan; S5. Use the established three-dimensional aircraft situation deduction model to deduce the flight situation of the aircraft under different weather conditions; S6. Based on the simulation results, assess the risk of the aircraft under different weather conditions; S7. Output the situation simulation results and risk assessment report of the aircraft under different weather conditions.

2. The method for potential deduction and risk assessment of digital twins of aircraft in a complex meteorological environment according to claim 1 is characterized by: The weather data includes wind direction angle parameters, wind speed parameters, temperature parameters, air pressure parameters and humidity parameters.

3. The method for potential deduction and risk assessment of digital twins of aircraft in a complex meteorological environment according to claim 2 is characterized by: The meteorological model includes the calculation of the effect of wind direction on the lateral force of the aircraft and the calculation of the effect of temperature on air density, as follows: ， Where: is the lateral force, is the lateral force coefficient, is the air density, is the aircraft speed, is the frontal area of ​​the aircraft, is the wind direction angle; ， Where: is the air density, is the air pressure, is the gas constant, For the temperature.

4. The method for potential deduction and risk assessment of digital twins of aircraft in a complex meteorological environment according to claim 3 is characterized by: The three-dimensional aircraft situation deduction model includes an aircraft dynamics model, a weather impact model and a flight environment model. The aircraft dynamics model is used to describe the motion state and force conditions of the aircraft; the weather impact model is used to describe the impact of weather conditions on the aircraft; and the flight environment model is used to describe the flight environment in which the aircraft is located.

5. The method for potential deduction and risk assessment of digital twins of aircraft in a complex meteorological environment according to claim 4 is characterized in that: The risk assessment includes flight safety risk assessment, flight performance risk assessment and flight mission risk assessment, where the flight safety risk assessment is calculated as follows: ， In the formula, For flight safety risks, is the probability of aircraft component failure, is the impact coefficient of the fault on flight safety.

6. The method for potential deduction and risk assessment of digital twins of aircraft in complex meteorological environments according to claim 5 is characterized by: The flight safety risk assessment is used to assess the flight safety risk of an aircraft under different weather conditions; the flight performance risk assessment is used to assess the flight performance risk of an aircraft under different weather conditions; and the flight mission risk assessment is used to assess the flight mission risk of an aircraft under different weather conditions.

7. The method for potential deduction and risk assessment of digital twins of aircraft in complex meteorological environments according to claim 6 is characterized by: The preprocessing in step S1 includes removing noise and outliers to improve the accuracy and reliability of the data.

8. The method for potential deduction and risk assessment of digital twins of aircraft in complex meteorological environments according to claim 7 is characterized by: The aircraft is one of an airplane, a helicopter or a drone.

9. The method for potential deduction and risk assessment of digital twins of aircraft in complex meteorological environments according to claim 8 is characterized by: The method is integrated with the navigation system and control system of the aircraft to provide real-time decision support for the safe flight of the aircraft. The method realizes remote monitoring and management through the Internet and satellite communication.

10. The method for potential deduction and risk assessment of digital twins of aircraft in complex meteorological environments according to claim 9, characterized in that: In step S7, when the risk assessment report result exceeds the set threshold, an early warning signal is issued, and the early warning signal is in the form of an audible and visual alarm or a text message notification.

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