Aircraft wing design method, terminal device and storage medium

Abstract

The present invention discloses an aircraft wing design method, terminal device, and storage medium. The method obtains the coordinates of wing boundary grid points, sorts the grid point coordinates, determines the adjacency relationship between grid points on the wing boundary based on the sorting result, and divides the wing boundary into n segments based on the adjacency relationship. The method then determines whether the n-segment cycle of the wing boundary has ended. If so, the cycle ends. Otherwise, a Vandermonde matrix is ​​constructed for each segment of the boundary curve. The polynomial degree of the i-th segment boundary curve is determined, and the polynomial Vandermonde matrix is ​​normalized. The polynomial coefficients are calculated using the normalized Vandermonde matrix to determine the high-order polynomial curve of the i-th segment of the wing. The method effectively reduces the error between the calculated shape and the actual shape, thereby greatly improving the accuracy of the computational simulation.

Description

Technical Field

[0001] The present invention relates to aircraft design technology, in particular to an aircraft wing design method, terminal equipment and storage medium. Background Art

[0002] The airfoil, commonly known as the wing profile or blade cross-section, is one of the core factors affecting the overall performance of an aircraft. The airfoil is a fundamental element in the design of aerodynamic surfaces such as aircraft wings, tail fins, missile aerofoil, helicopter rotors, propellers, and wind turbine blades. It directly influences the aerodynamic performance of an aircraft, including key aerodynamic characteristics such as lift, drag, and pitching moment. The aerodynamic characteristics of the airfoil also directly affect the maneuverability and stability of an aircraft. A well-designed airfoil can provide sufficient control torque, ensuring stability and maneuverability under various flight conditions, thereby improving flight safety.

[0003] In addition, the airfoil is closely related to the energy conservation, emission reduction and consumption reduction of aircraft. Optimizing the airfoil design is one of the effective measures to reduce drag, energy saving and fuel consumption. The airfoil design determines the lift-to-drag ratio of the aircraft [Li Yunpeng, Han Yongzhi. Research progress on the design of lift-enhancing devices based on laminar flow wings [J]. Progress in Aeronautical Engineering, 2021, 12(4): 1-11.], that is, the ratio of lift to drag. The larger the lift-to-drag ratio, the higher the flight efficiency, which can provide a longer range under limited fuel conditions and reduce environmental pollution [ALLISON E, KROO I, STURDZA P, et al. Aircraft conceptual design with natural laminar flow [C] ∥ The 27th International Congress of the Aeronautical Sciences. UK: Optimage, 2010: 1-2.]. Excellent airfoil design can achieve a high lift-to-drag ratio, effectively reduce fuel consumption, reduce carbon emissions, increase range and endurance, which is crucial to improving the flight efficiency and economy of the aircraft.

[0004] Key airfoil parameters directly impact its aerodynamic and drag reduction performance. For example, airfoil thickness, the maximum distance between the upper and lower surfaces perpendicular to the chord line, directly affects the airfoil's drag and structural strength. Camber, the maximum distance between the mid-arc and the chord line, influences lift generation. The trailing edge angle, the angle between the tangents of the upper and lower surfaces at the trailing edge, influences the airflow separation and control torque of the airfoil. Even small changes in these parameters can produce significant differences in lift and drag calculations. Therefore, numerical calculations require a close approximation of the airfoil design, which involves accurate representation of the airfoil.

[0005] Real airfoils are composed of curves or arcs, exhibiting a certain degree of curvature. Numerical simulation methods used in airfoil design require using a mesh to discretize the physical space into a computational space, with the airfoil's curves serving as the "wall" boundaries of the computational space. However, the structured, unstructured, or Cartesian grids commonly used in engineering applications are all composed of geometric shapes such as quadrilaterals, triangles, tetrahedrons, and hexahedrons. These airfoil's curved boundaries are treated as straight lines, or numerical methods are used to represent and approximate them. This representation and approximation imparts a certain degree of curvilinearity to the wall boundary, but the accuracy of the curved boundary representation determines the degree of approximation between the numerical representation and the real airfoil. Low-order curved boundary representation methods cannot accurately represent the curved boundary of an aircraft surface, resulting in numerical simulations that may not accurately reflect the actual airfoil shape. Furthermore, slight differences in key parameters between the numerical simulation and the real airfoil directly affect the accuracy of aerodynamic calculations, such as lift and drag, leading to inaccurate numerical simulations and a failure to reflect the airfoil's true performance.

[0006] Currently, the commonly used curve boundary expressions include polynomial curves, cubic spline curves and Bezier curves. The design of polynomial curves is simple, and polynomial expressions of different orders can be obtained through known point information, and can achieve Continuous. In contrast, the cubic spline curve can do this because it limits the values ​​at the endpoints and the first and second order derivatives. Continuous. Li Ming [Li Ming, Research on a High-Order Accuracy DG / FV Hybrid Algorithm Based on Hybrid Meshes, China Aerodynamics Research and Development Center, 2013.] used cubic spline curves to achieve high-order representations of curved boundaries in the discontinuous Galerkin (DG) / finite volume (FV) format. Unlike polynomials and cubic splines, Bézier curves [Bézier, Numerical Control: Mathematics and Applications, McGraw-Hill, 1972.] are essentially fitting methods, typically passing only the first and last control points. Gao and Wang [Gao H, Wang Z, Liu Y, A Study of Curved Boundary Representations for 2D High Order Euler Solvers. J SciComput, 2010, 44: 323–336.] et al. used Bézier curves within the framework of the spectral volume format to achieve third-order representations of curved boundaries. For each element, in addition to the two endpoints on the curve boundary, two midpoints must be determined using the tangent vectors at the endpoints to construct a local Bezier curve representation. However, this method requires the analytical representation of the curve to be known, and further refinement is needed for arbitrary curve configurations.

[0007] The segmentation idea can effectively improve the fit between the standard cubic spline interpolation curve and the analytical surface, but it still has many limitations. First, the polynomial order of the cubic spline interpolation curve is fixed at 3. If you want to further improve the order of the curve expression, you will face a more complicated derivation; second, whether it is the standard or segmented cubic spline interpolation method, it is necessary to manually give boundary conditions. The current mainstream approach is to impose natural boundary conditions on the starting point and end point of the curve, but for different curve configurations, this human factor will lead to potential errors; finally, although based on the segmentation idea, the constructed , and , The continuous curve significantly reduces the geometric error of the interpolation curve, but it will cause the error to rise at the intersection of the segments and achieve and The premise of continuity is

[0008] ;

[0009] If the above conditions cannot be met, continuity cannot be guaranteed and may even lead to calculation failure. Summary of the Invention

[0010] The technical problem to be solved by the present invention is to provide an aircraft wing design method, terminal equipment and storage medium to address the shortcomings of the existing technology, so that the wing boundary can be more accurately fitted into reality.

[0011] To solve the above technical problems, the technical solution adopted by the present invention is: a method for designing an aircraft wing, comprising the following steps:

[0012] S1. Obtain the coordinates of the grid points on the wing boundary, sort the grid point coordinates, determine the adjacent relationship between the grid points on the wing boundary based on the sorting result, and divide the wing boundary into n segments based on the adjacent relationship;

[0013] S2. Determine whether the n-segment loop of the wing boundary is completed. If so, then end; otherwise, construct a Vandermonde matrix for the i-th segment boundary curve;

[0014] S3. Determine the polynomial degree of the i-th segment boundary curve. If it is cubic, normalize the cubic polynomial Vandermonde matrix. If it is quartic, normalize the quartic polynomial Vandermonde matrix. If it is quintic, normalize the quintic polynomial Vandermonde matrix.

[0015] S4. Calculate polynomial coefficients using the normalized Vandermonde matrix to determine a high-order polynomial curve for the i-th section of the airfoil;

[0016] S5. Add 1 to the value of i and return to step S2.

[0017] In step S1, the specific implementation process of dividing the wing boundary into n segments according to the adjacent relationship includes: for the local wing boundary, if the distance between adjacent reference points is and There is a change in size, that is, from becomes , or from becomes , then segment at the changing position so that and The points are located on different segments; is the difference between the horizontal coordinates of the i-th reference point and the i-1-th reference point, is the difference between the ordinates of the i-th reference point and the i-1-th reference point.

[0018] For a fifth-degree polynomial, the Vandermonde matrix The expression is:

[0019] ;

[0020] For a fifth-order polynomial, the normalized expression of the Vandermonde matrix is:

[0021] ;

[0022] in, is the normalized parameter in the x direction, 、 、 、 Respectively the square, cubic, fourth and fifth powers of ~ are the ordinates of the six reference points, and a~f are the unknown coefficients of the quintic polynomial.

[0023] As an inventive concept, the present invention also provides a terminal device, including a memory, a processor, and a computer program stored in the memory; the processor executes the computer program to implement the steps of the above method.

[0024] As an inventive concept, the present invention also provides a computer-readable storage medium having a computer program / instruction stored thereon; the computer program / instruction implements the steps of the above method when executed by a processor.

[0025] As an inventive concept, the present invention also provides a computer program product, comprising a computer program / instruction; when the computer program / instruction is executed by a processor, the steps of the above method are implemented.

[0026] Compared with the prior art, the present invention has the following beneficial effects:

[0027] 1. Although the airfoil is supposed to be curved, it is composed of line segments after mesh discretization, which is somewhat different from the actual curved shape of the aircraft wing. The method of the present invention can restore the curved shape of the aircraft wing itself. Therefore, the result calculated by the method of the present invention is more accurate than the shape composed of line segments and is closer to the actual state of the actual airfoil in flight.

[0028] 2. In the prior art, during the meshing stage, the boundaries of irregular curves are directly replaced by line segments, which inevitably results in an approximate error. This makes the design using line segments inaccurate, and the estimated result is not the result of the true airfoil, but rather an approximate airfoil formed by line segments. By adopting the method of the present invention, the curve is restored starting from the line segments, and the shape of the airfoil is restored, effectively reducing the error between the calculated shape and the actual shape, thereby greatly improving the accuracy of the computational simulation. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Figure 1 It is a quadrilateral mesh NACA0012 airfoil;

[0030] Figure 2 Schematic diagram of the reference point selection method for expressing polynomial curves of different degrees;

[0031] Figure 3 The overall situation of three polynomial interpolation curves under different reference point distributions; (a) 80 reference points, (b) 140 reference points;

[0032] Figure 4 The local cases of three polynomial interpolation curves under different reference point distributions; (a) 80 reference points, (b) 140 reference points;

[0033] Figure 5 Geometric error distribution of polynomial and cubic spline interpolation curves under different reference point distributions; (a) 80 reference points, (b) 140 reference points;

[0034] Figure 6 Schematic diagram of the relative position relationship of normalized parameter points of third to fifth order polynomials;

[0035] Figure 7 Condition numbers and condition number reduction factors before and after planning for Vandermonde matrices of polynomials of degree 3 to 5; (a) cubic polynomial, (b) quartic polynomial, (c) quintic polynomial, (d) condition number reduction factor;

[0036] Figure 8 This is a flow chart of a method according to an embodiment of the present invention;

[0037] Figure 9 Comparison of the effects of polynomial interpolation curve improvement before and after improvement under different reference point distributions; (a) 80 reference points, (b) 140 reference points;

[0038] Figure 10 The geometric error distribution before and after the polynomial interpolation curve is improved under different reference point distributions; (a) 80 reference points, (b) 140 reference points;

[0039] Figure 11 Performance of the improved cubic spline curve and polynomial curve near different positions; (a) position 1, (b) position 2, (c) position 3, (d) position 4;

[0040] Figure 12 The improved cubic spline and polynomial curve for the NACA0012 airfoil fit well at different locations; (a) overall curve, (b) local location 1, (c) local location 2, and (d) local location 3. DETAILED DESCRIPTION

[0041] To make the objectives, technical solutions, and advantages of the embodiments of the present invention more clear, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings 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 making creative efforts shall fall within the scope of protection of the present invention.

[0042] Example 1

[0043] The airfoil curved boundary expression requires the use of a curve function to represent the boundary of the airfoil's geometric model, which involves the mapping from the geometric model to the computational model.

[0044] Mapping the geometric model to the computational model requires three steps: generating a mesh, building a coordinate system, and calculating coordinates. Figure 1 Taking the NACA0012 airfoil shown in the figure as an example, the three steps are explained.

[0045] 1. Generate a mesh

[0046] like Figure 1 As shown in the figure, firstly, the geometric model boundary of the NACA0012 airfoil is filled with points for discretization of the geometric boundary. These points are called grid points, and adjacent grid points are connected to form grid edges. After the grid edges on the geometric boundary are formed, the mesh generation software can be used to generate the mesh of the external calculation area of ​​the NACA0012 airfoil, as shown in the figure. Figure 1 As shown in the figure, a quadrilateral mesh is generated, but a triangular mesh can also be generated. The mesh edges in the computational model are straight line segments, while the airfoil boundaries in the geometric model are curved line segments. Therefore, the mesh cannot directly coincide with the curved boundaries.

[0047] 2. Constructing the coordinate system

[0048] You need to construct the XOY plane. Set the leading edge of the NACA0012 airfoil to point O. Set the x-axis along the chord line of the NACA0012 airfoil, the line connecting the leading and trailing edges, with the positive x-axis direction. Set the y-axis perpendicular to the x-axis through point O, with the positive y-axis direction pointing upward.

[0049] 3. Calculate coordinates

[0050] For each grid point in the calculation model, the grid coordinates of the grid point in the XOY plane are calculated according to the grid scale. , since the grid points strictly fall on the geometric boundaries, the coordinates of the grid points is accurate, while the coordinates on other geometric boundaries except grid points need to be approximated by the curved boundary expression function.

[0051] After completing the above three steps, the curved boundary expression function can be constructed through numerical methods.

[0052] The process of expressing curved boundaries requires constructing a curved boundary expression function. The coordinates of the grid points that strictly fall on the geometric boundary are known. and , these two grid points are adjacent, then the curved boundary expression function can be constructed , It can be approximated and The coordinates of any point on the curved boundary between two grid points ,in . Get all The expression can fully express the curve boundary.

[0053] by and The standard polynomial function is illustrated by the curved boundary between The construction method of , the standard cubic, quartic and quintic polynomial forms can be expressed as:

[0054] ;

[0055] The three orders of polynomials contain 4, 5, and 6 unknowns respectively. Therefore, the corresponding number of reference points is required for the polynomial expression of each local surface. Figure 2 Detailed description of the parameter point selection methods used in the embodiments of the present invention under three conditions is shown in FIG.

[0056] On this basis, we need to solve the unknown coefficients of the polynomial. Taking the fifth-order polynomial as an example, assuming that the six reference points are to , we can get the following Vandermonde equations:

[0057] ;

[0058] The system is a well-solved set of equations. The embodiment of the present invention uses the SVD method to calculate the matrix inverse and then obtain the polynomial coefficients.

[0059] The following shows the curve expression effects of three different order polynomials. Figure 3 As shown in the figure, overall, smooth cylindrical surface curves can be obtained based on the three polynomials, but Figure 4From the local enlarged images of the left and right endpoints shown in the figure, it can be seen that the cubic to quintic polynomials all show obvious errors near the endpoints, and the errors gradually increase with the increase of the degree of the polynomial.

[0060] In order to quantitatively show the geometric errors of the polynomial interpolation curve at different positions, Figure 5 The error distribution of three polynomial curves and standard cubic spline curve for the upper surface of the cylinder is statistically analyzed.

[0061] It can be seen that both the polynomial interpolation and the standard cubic spline interpolation curves have higher geometric errors near the left and right endpoints of the cylinder, while the errors in the middle are lower. Furthermore, as the degree of the polynomial increases, the geometric error in the middle gradually decreases. The geometric error of the cubic spline interpolation curve is between that of the cubic and quartic polynomial curves, but significantly higher than that of the quintic polynomial curve.

[0062] The advantages of the embodiments of the present invention are described below through experimental data.

[0063] The improved piecewise high-degree polynomial method involves segmenting the airfoil curve and normalizing the Vandermonde matrix when solving it. These two steps can reduce the calculation error of the standard polynomial method at the extreme positions of the airfoil curve.

[0064] Although the polynomial interpolation curve is simple to implement and can be easily extended to the fourth and fifth order, at extreme positions with high sensitivity to the x-coordinate, such as near the left and right end points of the cylinder, the reconstructed curve will have high geometric errors regardless of whether the cubic, fourth, or fifth order polynomial is used.

[0065] The improved high-order polynomial method will use the segmentation idea to segment a standard curve. The specific segmentation method is to compare the local and If the relationship between adjacent reference points and There is a change in size, that is, from becomes , or from becomes , then segment at the changing position so that and The points are located on different segments. After segmentation, the specific form of the curve polynomial can be determined. Note that polynomial interpolation curves do not require any artificial conditions, so no complex processing is required between segments.

[0066] Improved Vandermonde matrix normalization strategy:

[0067] From the Vandermonde equations, we know that the solution of the unknown coefficients of the polynomial requires the calculation of the inverse of the Vandermonde matrix. However, in actual situations, the condition number of this matrix is ​​often too large. For example, assuming that the six required parameter points are located at the extreme positions of the leading edge of the airfoil, they are

[0068]

[0069] At this time, the corresponding local Vandermonde system retaining 6 significant digits can be expressed as

[0070] ;

[0071] It can be seen that as the power exponent of the polynomial increases, the column elements of the matrix almost tend to 0, which may cause excessive errors in the matrix inverse obtained by the SVD method. However, if a reasonable normalization parameter is selected for the Vandermonde matrix , and starting from the second column of the matrix, use , , , and After normalization, the new Vandermonde system can be expressed as

[0072] ;

[0073] In the embodiment of the present invention, the normalized expressions of the cubic and quartic Vandermonde matrices are obtained by deleting the last column and the last row of the quintic Vandermonde matrix, or by deleting the last two columns and the last two rows.

[0074] Based on this idea, the parameters selected for the third to fifth degree polynomial curves are or The position relationship of Figure 6 In the figure, the black dots indicate the locations of the normalized parameters.

[0075] Taking the surface curve (circular boundary) of a cylinder with 140 reference points as an example, Figure 7 The figure shows the condition number of the Vandermonde matrix corresponding to each small segment of the polynomial curve before and after normalization, as well as the multiple by which the condition number decreases after optimization.

[0076] from Figure 7The results presented show that, regardless of whether the polynomial is cubic, quartic, or quintic, the condition number of the matrix can be significantly reduced by 2 to 3 orders of magnitude based on the given Vandermonde matrix normalization scheme. This will help improve the stability of the SVD method for solving matrix inverses, reduce inversion errors, and improve the accuracy of solving polynomial coefficients.

[0077] The method flow of this embodiment is as follows Figure 8 shown.

[0078] like Figure 8 As shown in Figure 2, the improved piecewise high-order polynomial method is divided into the following key steps:

[0079] 1. Read the coordinates of the airfoil boundary grid points ;

[0080] 2. Set the grid point coordinates Arrange in ascending order of x;

[0081] 3. Determine the adjacent relationship between grid points on the airfoil boundary according to the sorting, and and The relationship divides the airfoil curve into n segments;

[0082] 4. Loop through each of the n segments and determine whether the loop has ended. If not, go to step 5. If it has ended, go to step 11.

[0083] 5. Construct the Vandermonde matrix of the i-th segment of the curve;

[0084] 6. Determine the degree of the polynomial. If it is a cubic polynomial, go to step 7. If it is a cubic polynomial, go to step 8. If it is a cubic polynomial, go to step 9.

[0085] 7. Perform Vandermonde matrix normalization on the cubic polynomial curve and go to 10.

[0086] 8. Perform Vandermonde matrix normalization on the quartic polynomial curve and go to 10.

[0087] 9. Perform Vandermonde matrix normalization on the quintic polynomial curve and go to 10.

[0088] 10. Use the SVD method to solve the normalized Vandermonde matrix of the high-order polynomial curve to obtain the airfoil curve expression for the i-th segment, and go to 4;

[0089] 11. End.

[0090] Figure 9First, the fit between the polynomial interpolation curve and the analytical curve near the left and right endpoints of the cylindrical upper surface curve (circular boundary) before and after the improvement is demonstrated.

[0091] from Figure 9 It can be seen that regardless of whether there are 80 or 140 reference points distributed on the cylindrical surface, after improvement based on the segmentation idea, the third to fifth order polynomial curves fit the cylindrical analytical curve perfectly, with no obvious deviation at the left and right endpoints, which is a significant improvement compared to the standard polynomial curve. Figure 10 This is more clearly seen in the geometric error distribution of the cylinder surface shown in Figure 2. The improved multi-form interpolation curve significantly reduces the errors at the left and right endpoints, and at the boundary between segments, the geometric error of the improved cubic spline interpolation curve does not exceed that of the original curve.

[0092] Judging from the results obtained, reconstructing the curved surface expression based on the polynomial interpolation curve is an ideal strategy. After improving it in a segmented manner, it can effectively improve the fit between the curved surface and the analytical surface.

[0093] After improving the polynomial curve based on the idea of ​​segmented expression and matrix normalization, the fit between the reconstructed curve and the analytical curve was significantly improved, and the geometric error was reduced.

[0094] Figure 11 The performance of the improved cubic spline and polynomial curve at four different locations is shown when 140 reference points are distributed on the cylindrical surface.

[0095] The results show that the two improved cubic spline curves do not fit the analytical cylindrical curve well at four locations. In contrast, the polynomial curves, especially the quintic polynomial curve, fit the cylindrical surface very closely at the four locations shown.

[0096] On the basis of cylindrical curves, the embodiment of the present invention further considers the real airfoil in engineering applications - NACA0012 airfoil. The upper and lower surface curves of the airfoil have analytical expressions

[0097] .

[0098] The following will continue to demonstrate two types of improved curve expression effects at different positions.

[0099] from Figure 12As can be seen, for the NACA0012 airfoil, the improved polynomial curve exhibits a lower relative error with the analytical curve than the cubic spline curve near the displayed position. Therefore, these two typical shapes demonstrate the advantages of the improved polynomial curve over the cubic spline curve. The quintic polynomial curve, in particular, exhibits a lower geometric error and a higher degree of fit with the analytical curve, paving the way for the implementation of higher-order schemes on curved elements. Furthermore, this higher degree of fit with the analytical curve can largely overcome the problem of reconstructed curves passing through the first few mesh layers in high Reynolds number flows.

[0100] Example 2

[0101] Embodiment 2 of the present invention provides a measurement system corresponding to the above-mentioned embodiment 1. The measurement system may be a processing device for a client, such as a mobile phone, a laptop, a tablet computer, a desktop computer, etc., to execute the method of the above-mentioned embodiment.

[0102] The measurement system of this embodiment includes a memory, a processor, and a computer program stored in the memory; the processor executes the computer program in the memory to implement the steps of the method in the above-mentioned embodiment 1.

[0103] In some implementations, the memory may be a high-speed random access memory (RAM), and may also include a non-volatile memory, such as at least one disk storage.

[0104] In other implementations, the processor may be a central processing unit (CPU), a digital signal processor (DSP), or other general-purpose processors, which are not limited herein.

[0105] Although the preferred embodiments of the present application have been described, those skilled in the art may make additional changes and modifications to these embodiments once they have learned the basic creative concept. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments and all changes and modifications that fall within the scope of the present application.

[0106] Obviously, those skilled in the art may make various changes and modifications to this application without departing from the spirit and scope of this application. Thus, if these modifications and variations of this application fall within the scope of the claims of this application and their equivalents, this application is intended to include these modifications and variations.

Claims

1. A method for designing an aircraft wing, characterized in that: The following steps are involved: S1. Obtain the coordinates of the grid points on the wing boundary, sort the grid point coordinates, determine the adjacent relationship between the grid points on the wing boundary based on the sorting result, and divide the wing boundary into n segments based on the adjacent relationship; S2. Determine whether the n-segment loop of the wing boundary is completed. If so, then end; otherwise, construct a Vandermonde matrix for the i-th segment boundary curve; S3. Determine the polynomial degree of the i-th segment boundary curve. If it is cubic, normalize the cubic polynomial Vandermonde matrix. If it is quartic, normalize the quartic polynomial Vandermonde matrix. If it is quintic, normalize the quintic polynomial Vandermonde matrix. S4. Calculate polynomial coefficients using the normalized Vandermonde matrix to determine a high-order polynomial curve for the i-th section of the airfoil; S5. Add 1 to the value of i and return to step S2.

2. The aircraft wing design method according to claim 1, characterized in that: In step S1, the specific implementation process of dividing the wing boundary into n segments according to the adjacent relationship includes: For the wing boundary, if the distance between adjacent reference points is and There is a change in size, that is, from becomes , or from becomes , then segment at the changing position so that and The points are located on different segments; is the difference between the horizontal coordinates of the i-th reference point and the i-1-th reference point, is the difference between the ordinates of the i-th reference point and the i-1-th reference point.

3. The aircraft wing design method according to claim 1, characterized in that: For a quintic polynomial, the Vandermonde matrix The expression is: 。 4. The aircraft wing design method according to claim 1, characterized in that: For a fifth-order polynomial, the normalized expression of the Vandermonde matrix is: ； in, is the normalized parameter in the x direction, 、 、 、 Respectively the square, cubic, fourth and fifth powers of ~ are the ordinates of the six reference points, and a~f are the unknown coefficients of the quintic polynomial.

5. A terminal device comprising a memory, a processor, and a computer program stored in the memory; characterized in that: The processor executes the computer program to implement the steps of the method according to any one of claims 1 to 4.

6. A computer-readable storage medium having a computer program / instruction stored thereon; characterized in that: When the computer program / instructions are executed by a processor, the steps of the method according to any one of claims 1 to 4 are implemented.

7. A computer program product comprising a computer program / instructions; characterized in that When the computer program / instructions are executed by a processor, the steps of the method according to any one of claims 1 to 4 are implemented.

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