Method and system for modeling aerodynamic efficiency of nonlinear control surface of high-speed aircraft

Abstract

The embodiment of the invention provides a modeling method and system for aerodynamic efficiency of a nonlinear control surface of a high-speed aircraft, and the method comprises the steps: carrying out the numerical simulation of aerodynamic data of the high-speed aircraft at different control surface deflection angles through employing a computational fluid dynamics (CFD) method, building a control surface aerodynamic efficiency data set in a high-speed flight scene, comprising a sample set and a verification set; taking the sample set as an input variable, and constructing a high-speed aircraft nonlinear control surface aerodynamic efficiency prediction model; and performing verification and error evaluation on the constructed nonlinear control surface efficiency aerodynamic model of the high-speed aircraft by adopting the verification set, and updating model parameters to obtain a final control surface aerodynamic efficiency model. According to the method, the aerodynamic efficiency of the rapid nonlinear control surface of the high-speed aircraft can be rapidly predicted, and a rapid control surface aerodynamic efficiency prediction means is provided for design of a control system in a high-speed flight scene.

Description

Technical Field

[0001] This document relates to the technical field of aircraft aerodynamic design, and in particular to a method and system for modeling the aerodynamic efficiency of nonlinear control surfaces of high-speed aircraft. Background Art

[0002] At present, there are two main types of research methods for nonlinear unsteady aerodynamic modeling methods widely used in engineering: one is to establish traditional mathematical aerodynamic models related to aerodynamic forces and flight physical quantities (such as algebraic models, step response models, etc.), and the other is intelligent learning aerodynamic models (such as fuzzy logic method, support vector machine (SVM), etc.). Among them, the intelligent learning method can establish a multi-input and multi-output nonlinear aerodynamic model, but due to its "black box" attribute, the inherent physical meaning of the aerodynamic model is unclear, and there are potential risks in use. The mathematical method is to perform nonlinear aerodynamic modeling based on aerodynamic data, which has a clear physical meaning, high model accuracy, controllable model use risks, and has strong engineering application value.

[0003] During the flight of high-speed flight scenarios, the aircraft rudders need to be controlled in real time. Therefore, in the design of the aircraft control system, the accurate prediction of the rudder efficiency is a key factor. However, with the increasing demand for the maneuverability of high-speed aircraft, a larger rudder deflection angle is required for attitude control to meet the maneuverability requirements. When the rudder deflection angle is large, the deflected rudder will enter the shock wave interference area brought by the aircraft head, causing the rudder efficiency to show obvious nonlinear changes. The traditional linear rudder efficiency modeling method can no longer meet the existing engineering needs. Therefore, it is necessary to take advantage of the high accuracy of the nonlinear modeling method to establish a rudder aerodynamic efficiency model for high-speed flight scenarios. This model can quickly predict the aerodynamic efficiency of the aircraft rudder, thereby providing a fast aerodynamic prediction method for the control system design in high-speed flight scenarios. Summary of the invention

[0004] One or more embodiments of this specification provide a method for modeling aerodynamic efficiency of nonlinear control surfaces of high-speed aircraft, including:

[0005] Computational fluid dynamics (CFD) is used to numerically simulate the aerodynamic data of high-speed aircraft under different control surface deflection angles, and a data set of control surface aerodynamic efficiency under high-speed flight scenarios is established, including a sample set and a verification set.

[0006] Taking the sample set as input variable, a prediction model of aerodynamic efficiency of nonlinear control surface of high-speed aircraft is constructed.

[0007] The validation set is used to verify and evaluate the error of the constructed nonlinear control surface efficiency aerodynamic model of high-speed aircraft, update the model parameters, and obtain the final control surface aerodynamic efficiency model.

[0008] Furthermore, before numerical simulation, the aircraft mesh required for CFD numerical simulation is generated according to the characteristics of the high-speed aircraft. The specific method is as follows:

[0009] Use Pointwise mesh generation software to import high-speed aircraft digital models;

[0010] Generate grid line connectors at the edge of the aircraft digital model;

[0011] Distribute grid points on each grid line connector and encrypt them in areas with more separated flows;

[0012] Generate a mesh domain through the mesh line connector, and project the domain onto the digital model surface to make the mesh fit the body;

[0013] Generate grid blocks through grid surface domain to complete spatial grid generation;

[0014] Keep the aircraft body still, adjust the position of the control surface around the rotation axis according to the angle, repeat the above steps, and finally form the aircraft grid under different control surface deflection angles.

[0015] Furthermore, after the aircraft grid is generated, aerodynamic setting items are selected according to the characteristics of the high-speed aircraft to perform preliminary aerodynamic calculations. The aerodynamic setting items include: spatial discrete format, time advancement format, turbulence model, preprocessing and entropy correction to obtain aerodynamic force and preliminary flow field, and the preliminary flow field contains pressure, density, temperature, energy and velocity information; the grid is encrypted according to the obtained aerodynamic force and preliminary flow field until the aerodynamic force change is less than a preset value.

[0016] Furthermore, the aerodynamic data includes normal force, axial force and pitching moment.

[0017] Furthermore, taking the sample set as input variable, the specific method of constructing the aerodynamic efficiency prediction model of the nonlinear control surface of high-speed aircraft is as follows:

[0018] The deflection angle of the rudder surface is used as the basic variable of the aerodynamic model. Under the condition of fixed attack angle and sideslip angle, the deflection angle of the rudder surface is changed to obtain the curve of aerodynamic force changing with the deflection angle of the rudder surface.

[0019] The least square method is used to fit the curve of aerodynamic force with the deflection angle of the rudder surface to obtain the maximum order of the nonlinear aerodynamic model.

[0020] The pre-multiplication coefficient of the deflection angle of the control surface in the nonlinear aerodynamic model is expressed as a second-order polynomial. The sample set is used as the input variable to determine the parameters of the nonlinear aerodynamic model and obtain the aerodynamic efficiency prediction model of the nonlinear control surface of the high-speed aircraft.

[0021] Furthermore, the validation set is used to verify and evaluate the error of the constructed high-speed aircraft nonlinear control surface efficiency aerodynamic model. The specific methods are as follows:

[0022] The data in the validation set are input into the control surface efficiency aerodynamic model, and the model error is evaluated based on the mean square error between several points and the fitting points.

[0023] Furthermore, 80% of the data in the data set is used as a sample set, and the remaining 20% ​​of the data is used as a validation set.

[0024] One or more embodiments of this specification provide a high-speed aircraft nonlinear control surface aerodynamic efficiency modeling system, including:

[0025] Data acquisition module: used to numerically simulate the aerodynamic data of high-speed aircraft under different control surface deflection angles using the computational fluid dynamics method (CFD), and to establish a data set of control surface aerodynamic efficiency in high-speed flight scenarios, including a sample set and a verification set;

[0026] Model building module: used to build a high-speed aircraft nonlinear control surface aerodynamic efficiency prediction model with sample sets as input variables;

[0027] Model verification module: used to verify and evaluate the error of the constructed high-speed aircraft nonlinear control surface efficiency aerodynamic model using the verification set, update the model parameters, and obtain the final control surface aerodynamic efficiency model.

[0028] One or more embodiments of the present specification provide an electronic device, including:

[0029] processor; and,

[0030] A memory arranged to store computer executable instructions, which, when executed, cause the processor to implement the steps of the above-mentioned method for modeling the aerodynamic efficiency of nonlinear control surfaces of high-speed aircraft.

[0031] One or more embodiments of the present specification provide a storage medium for storing computer executable instructions, which, when executed, implement the steps of the above-mentioned method for modeling the aerodynamic efficiency of nonlinear control surfaces of high-speed aircraft.

[0032] By adopting the embodiment of the present invention, a model of the aerodynamic efficiency of the control surfaces in high-speed flight scenarios is established, which can quickly predict the aerodynamic efficiency of the fast nonlinear control surfaces of high-speed aircraft with a calculation time of milliseconds, and provide a fast control surface aerodynamic efficiency prediction method for the control system design in high-speed flight scenarios.

[0033] The above description is only an overview of the technical solution of the present invention. In order to more clearly understand the technical means of the present invention, it can be implemented according to the contents of the specification. In order to make the above and other purposes, features and advantages of the present invention more obvious and easy to understand, the specific implementation methods of the present invention are listed below. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] In order to more clearly illustrate one or more embodiments of this specification or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in this specification. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative labor.

[0035] Figure 1 A flowchart of a method for modeling aerodynamic efficiency of nonlinear control surfaces of a high-speed aircraft provided in one or more embodiments of this specification;

[0036] Figure 2 A schematic diagram of the distribution of aerodynamic samples of a high-speed aircraft nonlinear control surface aerodynamic efficiency modeling method provided in one or more embodiments of this specification;

[0037] Figure 3 A schematic diagram of the distribution of aerodynamic samples of a high-speed aircraft nonlinear control surface aerodynamic efficiency modeling method provided in one or more embodiments of this specification;

[0038] Figure 4 A schematic diagram of comparison between sample values ​​of control surfaces and modeling prediction values ​​of a high-speed aircraft nonlinear control surface aerodynamic efficiency modeling method provided in one or more embodiments of this specification;

[0039] Figure 5 A schematic diagram of the error distribution of a control surface aerodynamic efficiency model of a high-speed aircraft nonlinear control surface aerodynamic efficiency modeling method provided in one or more embodiments of this specification;

[0040] Figure 6 A schematic diagram of the composition of a high-speed aircraft nonlinear control surface aerodynamic efficiency modeling system provided in one or more embodiments of this specification;

[0041] Figure 7 A schematic diagram of the structure of an electronic device provided for one or more embodiments of this specification. DETAILED DESCRIPTION

[0042] In order to enable those skilled in the art to better understand the technical solutions in one or more embodiments of this specification, the following will be combined with the drawings in one or more embodiments of this specification to clearly and completely describe the technical solutions in one or more embodiments of this specification. Obviously, the described embodiments are only part of the embodiments of this specification, not all of the embodiments. Based on one or more embodiments of this specification, all other embodiments obtained by ordinary technicians in this field without creative work should fall within the scope of protection of this document.

[0043] Method Embodiment

[0044] According to an embodiment of the present invention, a method for modeling aerodynamic efficiency of nonlinear control surfaces of a high-speed aircraft is provided. Figure 1 A flowchart of a method for modeling the aerodynamic efficiency of a nonlinear control surface of a high-speed aircraft provided in one or more embodiments of this specification, such as Figure 1 As shown, the method for modeling aerodynamic efficiency of nonlinear control surfaces of high-speed aircraft according to an embodiment of the present invention specifically includes:

[0045] S1. Computational fluid dynamics (CFD) method is used to numerically simulate the aerodynamic data of high-speed aircraft under different control surface deflection angles, and a control surface aerodynamic efficiency dataset under high-speed flight scenarios is established, including a sample set and a verification set.

[0046] Before numerical simulation, the aircraft mesh required for CFD numerical simulation is generated according to the characteristics of high-speed aircraft. The specific method is as follows:

[0047] Pointwise mesh generation software is used to import the high-speed aircraft digital model; grid line connectors are generated at the edge of the aircraft digital model; grid points are distributed on each grid line connector and encrypted in areas with more separated flows; a grid surface domain is generated through the grid line connector, and the domain is projected onto the surface of the digital model to make the grid fit the body; a grid block is generated through the grid surface domain to complete the spatial grid generation; the aircraft body is kept stationary, and the rudder adjusts its position around the rotation axis according to the angle, and the above steps are repeated to finally form the aircraft grid under different rudder deflection angles.

[0048] After the aircraft grid is generated, aerodynamic setting items are selected according to the characteristics of the high-speed aircraft for preliminary aerodynamic calculations. The aerodynamic setting items include: spatial discrete format, time advancement format, turbulence model, preprocessing and entropy correction to obtain aerodynamic force and preliminary flow field. The preliminary flow field contains pressure, density, temperature, energy and velocity information. The grid is encrypted according to the obtained aerodynamic force and preliminary flow field until the aerodynamic force change is less than the preset value.

[0049] The flow field of high-speed aircraft at different rudder deflection angles is simulated to obtain the aerodynamic data of high-speed aircraft, including normal force, axial force and pitch moment. Based on the aerodynamic data, the rudder aerodynamic efficiency data is sorted into the data set required for nonlinear modeling, and 80% of the data in the data set is used as the sample set, and the remaining 20% ​​of the data is used as the verification set.

[0050] S2. Using the sample set as input variables, a prediction model for the aerodynamic efficiency of nonlinear control surfaces of high-speed aircraft is constructed.

[0051] The two-dimensional polynomial method is used to design the model framework. The rudder deflection angle is taken as the basic variable of the aerodynamic model. Under fixed angle of attack and sideslip angle, different rudder deflection angles are changed to obtain the aerodynamic force curve varying with the rudder deflection angle. The least squares method is used to fit the aerodynamic force curve varying with the rudder deflection angle to obtain the maximum order of the nonlinear aerodynamic model. The pre-multiplication coefficient of the rudder deflection angle in the nonlinear aerodynamic model is expressed as a second-order polynomial. The sample set is used as the input variable to determine the parameters of the nonlinear aerodynamic model, and the aerodynamic efficiency prediction model of the nonlinear rudder of a high-speed aircraft is obtained.

[0052] S3. Use the validation set to verify and evaluate the error of the constructed high-speed aircraft nonlinear control surface efficiency aerodynamic model, update the model parameters, and obtain the final control surface aerodynamic efficiency model.

[0053] The data in the validation set are input into the control surface efficiency aerodynamic model, and the model error is evaluated based on the mean square error between several points and the fitting points.

[0054] The following is a specific embodiment, which uses a nonlinear aerodynamic modeling method based on a high-speed flight scenario to model and predict the aerodynamic efficiency of the control surface in the longitudinal plane under a high-speed flight scenario:

[0055] Figure 2 This is a typical description of a high-speed flight scenario. As can be seen from the figure, the control surface of a high-speed aircraft is at the tail. Due to the high-pressure interference area caused by the shock wave at the head of the high-speed aircraft, when the control surface deflects beyond a certain angle, the aerodynamic efficiency of the control surface will suddenly increase with nonlinear characteristics, such as Figure 3 ,The prediction of aerodynamic efficiency of control surfaces of high-speed aircraft is a ,challenge for control system design.

[0056] First, it is necessary to make a preliminary plan for the input and output of the aerodynamic model. Since only the aerodynamic force prediction in the longitudinal plane is considered in this scenario, two variables are required as input, namely the incoming flow angle of attack α and the rudder deflection angle δ. The output must consider the two direct forces and one moment of the aircraft, so the output of the model is three quantities, namely normal force, axial force, and pitch moment.

[0057] Then, numerical simulation is used to obtain the aerodynamic force and torque values ​​under different attack angles and rudder deflection angles, as shown in Table 1:

[0058] Table 1

[0059] Ma Angle of attack (°) Rudder deflection angle (°) 6.0 -4、-2、0、2、4 ±20、±15、±10、±5、±2、0

[0060] Then, from the perspective of aerodynamic characteristics, the aerodynamic force / torque curve with the rudder angle change when the angle of attack α = 0° was preliminarily fitted, and it was found that its change law basically conforms to the cubic polynomial, so the highest order of the polynomial was determined to be 3. Therefore, the basic form of the rudder efficiency model is listed below. In the formula, the rudder angle δ is used as the independent variable, and the function containing the angle of attack α is used as the unknown coefficient. The two types of variables are multiplied to form a nonlinear characteristic. The formula is as follows:

[0061] Cx=f0(α)+f1(α)δ+f2(α)δ 2 +f3(α)δ 3 ;

[0062] In the formula: α is the incoming flow angle of attack (°); δ is the rudder deflection angle (°); Cx is the predicted value of aerodynamic force / torque (including normal force, axial force, and pitching moment).

[0063] Next, it is necessary to determine the undetermined function f(x) of the independent variable rudder deflection angle δ. Fit the aerodynamic force / torque curves with the rudder deflection angle at the angles of attack α of -4°, -2°, 0°, 2°, and 4°, record the corresponding f(x) values, and then perform polynomial fitting on the f(x) values ​​with the angle of attack α. It is found that f(x) and α are mainly reflected in a quadratic polynomial relationship, so its maximum order is determined to be 2, and the parameters c0, c1, and c2 are determined by polynomial fitting. Its basic form is:

[0064] f(α)=c0+c1α+c2α 2 ;

[0065] Since the normal force, axial force, and pitching moment show different changing rules, each aerodynamic coefficient is different. The specific values ​​are shown in Table 2:

[0066] Table 2

[0067]

[0068] After determining the parameter values, the aerodynamic model is verified. The verification conditions are shown in Table 3:

[0069] Table 3

[0070]

[0071] Make sure that the verification conditions are more than the number of samples. Substitute the different attack angles and rudder deflection angles in Table 3 into the rudder surface efficiency aerodynamic model to verify the model. Figure 4 This is a comparison between the predicted values ​​of the aerodynamic model and the sample values. It can be seen from the figure that within the sample coverage range, the aerodynamic model can predict the aerodynamic force well, which verifies the rationality of the nonlinear control surface aerodynamic efficiency model.

[0072] Finally, the model accuracy and generalization characteristics of the nonlinear control surface aerodynamic efficiency model are evaluated.

[0073] The prediction error of the aerodynamic model is defined as follows:

[0074]

[0075] In the formula: C_error is the prediction error; Cpre is the predicted value under each working condition; Csam is the sample value under each working condition.

[0076] Figure 5 The error statistics of the rudder effect aerodynamic model in the whole sample range are shown in the figure. The figure shows the prediction error of the polynomial model. It can be seen from the figure that the prediction effect of the aerodynamic model is very good under most working conditions. Within the sample range, the error can basically reach less than 2%. In the out-of-sample range (generalization), the prediction error will increase and can reach an error of about 12%, which can meet the engineering needs.

[0077] The above is a preliminary test of the aerodynamic efficiency model of the nonlinear control surface of a high-speed aircraft. From the test results, it can be seen that the aerodynamic model established by this method has a strong ability to predict the aerodynamic efficiency of nonlinear control surfaces.

[0078] The beneficial effects of the present invention are as follows:

[0079] By adopting the embodiment of the present invention, a model of the aerodynamic efficiency of the control surfaces in high-speed flight scenarios is established, which can quickly predict the aerodynamic efficiency of the fast nonlinear control surfaces of high-speed aircraft with a calculation time of milliseconds, and provide a fast control surface aerodynamic efficiency prediction method for the control system design in high-speed flight scenarios.

[0080] System Example

[0081] According to an embodiment of the present invention, a high-speed aircraft nonlinear control surface aerodynamic efficiency modeling system is provided. Figure 6 A schematic diagram of a high-speed aircraft nonlinear control surface aerodynamic efficiency modeling system provided in one or more embodiments of this specification is shown in FIG. Figure 6 As shown, the high-speed aircraft nonlinear control surface aerodynamic efficiency modeling system according to an embodiment of the present invention specifically includes:

[0082] Data acquisition module 60: used to numerically simulate aerodynamic data of high-speed aircraft under different control surface deflection angles using computational fluid dynamics (CFD) method, and establish a control surface aerodynamic efficiency data set under high-speed flight scenarios, including a sample set and a verification set;

[0083] Model building module 62: used to build a high-speed aircraft nonlinear control surface aerodynamic efficiency prediction model using the sample set as input variables;

[0084] Model verification module 64: used to verify and evaluate the error of the constructed high-speed aircraft nonlinear control surface efficiency aerodynamic model using the verification set, update the model parameters, and obtain the final control surface aerodynamic efficiency model.

[0085] The embodiment of the present invention is a system embodiment corresponding to the above-mentioned method embodiment. The specific operations of each module can be understood by referring to the description of the method embodiment, which will not be repeated here.

[0086] Device Example 1

[0087] An embodiment of the present invention provides an electronic device, such as Figure 7 As shown, it includes: a memory 70, a processor 72, and a computer program stored in the memory 70 and executable on the processor 72. When the computer program is executed by the processor 72, the following method steps are implemented:

[0088] S1. Use computational fluid dynamics (CFD) to numerically simulate the aerodynamic data of high-speed aircraft under different control surface deflection angles, and establish a data set of control surface aerodynamic efficiency under high-speed flight scenarios, including a sample set and a validation set;

[0089] S2. Using the sample set as input variables, a prediction model for the aerodynamic efficiency of nonlinear control surfaces of high-speed aircraft is constructed;

[0090] S3. Use the validation set to verify and evaluate the error of the constructed high-speed aircraft nonlinear control surface efficiency aerodynamic model, update the model parameters, and obtain the final control surface aerodynamic efficiency model.

[0091] Device Example 2

[0092] S1. Use computational fluid dynamics (CFD) to numerically simulate the aerodynamic data of high-speed aircraft under different control surface deflection angles, and establish a data set of control surface aerodynamic efficiency under high-speed flight scenarios, including a sample set and a validation set;

[0093] S2. Using the sample set as input variables, a prediction model for the aerodynamic efficiency of nonlinear control surfaces of high-speed aircraft is constructed;

[0094] S3. Use the validation set to verify and evaluate the error of the constructed high-speed aircraft nonlinear control surface efficiency aerodynamic model, update the model parameters, and obtain the final control surface aerodynamic efficiency model.

[0095] An embodiment of the present invention provides a computer-readable storage medium, on which a program for implementing information transmission is stored. When the program is executed by the processor 72, the following method steps are implemented:

[0096] The computer-readable storage medium in this embodiment includes, but is not limited to, ROM, RAM, magnetic disk or optical disk, etc.

[0097] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or replace some or all of the technical features therein with equivalents. However, these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. A method for modeling the aerodynamic efficiency of nonlinear control surfaces of high-speed aircraft, characterized in that: include: Computational fluid dynamics (CFD) is used to numerically simulate the aerodynamic data of high-speed aircraft under different control surface deflection angles, and a data set of control surface aerodynamic efficiency under high-speed flight scenarios is established, including a sample set and a verification set. Taking the sample set as input variable, a prediction model of aerodynamic efficiency of nonlinear control surface of high-speed aircraft is constructed. The validation set is used to verify and evaluate the error of the constructed nonlinear control surface efficiency aerodynamic model of high-speed aircraft, update the model parameters, and obtain the final control surface aerodynamic efficiency model.

2. The method according to claim 1, characterized in that Before numerical simulation, the aircraft mesh required for CFD numerical simulation is generated according to the characteristics of high-speed aircraft. The specific method is as follows: Use Pointwise mesh generation software to import high-speed aircraft digital models; Generate grid line connectors at the edge of the aircraft digital model; Distribute grid points on each grid line connector and encrypt them in areas with more separated flows; Generate a mesh domain through the mesh line connector, and project the domain onto the digital model surface to make the mesh fit the body; Generate grid blocks through grid surface domain to complete spatial grid generation; Keep the aircraft body still, adjust the position of the control surface around the rotation axis according to the angle, repeat the above steps, and finally form the aircraft grid under different control surface deflection angles.

3. The method according to claim 2, characterized in that After the aircraft grid is generated, aerodynamic setting items are selected according to the characteristics of the high-speed aircraft for preliminary aerodynamic calculations. The aerodynamic setting items include: spatial discrete format, time advancement format, turbulence model, preprocessing and entropy correction to obtain aerodynamic force and preliminary flow field. The preliminary flow field contains pressure, density, temperature, energy and velocity information. The grid is encrypted according to the obtained aerodynamic force and preliminary flow field until the aerodynamic force change is less than the preset value.

4. The method according to claim 1, characterized in that: The aerodynamic force data includes normal force, axial force and pitching moment.

5. The method according to claim 1, characterized in that Taking the sample set as input variable, the specific method of constructing the aerodynamic efficiency prediction model of the nonlinear control surface of high-speed aircraft is as follows: The deflection angle of the rudder surface is used as the basic variable of the aerodynamic model. Under the condition of fixed attack angle and sideslip angle, the deflection angle of the rudder surface is changed to obtain the curve of aerodynamic force changing with the deflection angle of the rudder surface. The least square method is used to fit the curve of aerodynamic force with the deflection angle of the rudder surface to obtain the maximum order of the nonlinear aerodynamic model. The pre-multiplication coefficient of the deflection angle of the control surface in the nonlinear aerodynamic model is expressed as a second-order polynomial. The sample set is used as the input variable to determine the parameters of the nonlinear aerodynamic model and obtain the aerodynamic efficiency prediction model of the nonlinear control surface of the high-speed aircraft.

6. The method according to claim 1, characterized in that The validation set is used to verify and evaluate the error of the constructed high-speed aircraft nonlinear control surface efficiency aerodynamic model. The specific method is as follows: The data in the validation set are input into the control surface efficiency aerodynamic model, and the model error is evaluated based on the mean square error between several points and the fitting points.

7. The method according to claim 1, characterized in that 80% of the data in the dataset is used as a sample set, and the remaining 20% ​​of the data is used as a validation set.

8. A high-speed aircraft nonlinear control surface aerodynamic efficiency modeling system, characterized in that: include: Data acquisition module: used to numerically simulate the aerodynamic data of high-speed aircraft under different control surface deflection angles using the computational fluid dynamics method (CFD), and to establish a data set of control surface aerodynamic efficiency in high-speed flight scenarios, including a sample set and a verification set; Model building module: used to build a high-speed aircraft nonlinear control surface aerodynamic efficiency prediction model with sample sets as input variables; Model verification module: used to verify and evaluate the error of the constructed high-speed aircraft nonlinear control surface efficiency aerodynamic model using the verification set, update the model parameters, and obtain the final control surface aerodynamic efficiency model.

9. An electronic device, characterized in that: include: processor; as well as, A memory arranged to store computer executable instructions, which, when executed, cause the processor to implement the steps of the method for modeling aerodynamic efficiency of nonlinear control surfaces of high-speed aircraft according to any one of claims 1 to 7.

10. A storage medium, characterized in that: Used to store computer executable instructions, which, when executed, implement the steps of the method for modeling the aerodynamic efficiency of nonlinear control surfaces of high-speed aircraft as described in any one of claims 1 to 7.

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