Aircraft wing design method, terminal equipment and storage medium

Abstract

The invention discloses an aircraft wing design method, terminal equipment and a storage medium, and the method comprises the steps: obtaining the coordinates of grid points of a wing boundary, sorting the coordinates of the grid points, determining the adjacent relation between the grid points on the wing boundary according to the sorting result, and dividing the wing boundary into n segments according to the adjacent relation; judging whether n sections of circulation of the wing boundary are finished or not, and if yes, finishing; otherwise, constructing a Vandermonde matrix for each section of boundary curve; judging the polynomial times of the i-th section of boundary curve, and normalizing a polynomial Vandermonde matrix; and calculating a polynomial coefficient by using the normalized Vandermonde matrix, and determining a high-order polynomial curve of the ith section of wing. According to the method, the error between the calculation shape and the actual shape is effectively reduced, so that the calculation simulation precision is greatly improved.

Description

Technical Field

[0001] The present invention relates to the technology of aircraft design, in particular to an aircraft wing design method, a terminal device and a storage medium. Background Technique

[0002] The airfoil, commonly known as the wing section or blade section, is one of the core factors affecting the comprehensive performance of an aircraft. The airfoil is the basic element for the aerodynamic shape design of aircraft wings, tails, missile wing surfaces, helicopter rotors, propellers, and wind turbine blades, etc. It directly affects the aerodynamic performance of the aircraft, including key aerodynamic characteristics such as lift, drag, and pitching moment. The aerodynamic characteristics of the airfoil can also directly affect the maneuverability and stability of the aircraft. A good airfoil design can provide sufficient control moment to ensure the stability and maneuverability of the aircraft under various flight conditions, thereby improving flight safety.

[0003] In addition, the airfoil is also closely related to the energy conservation, emission reduction, and consumption reduction of the aircraft. Optimizing the airfoil design is one of the effective measures to reduce drag and energy consumption and reduce 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 augmentation devices based on laminar wings [J]. Advances in Aeronautical Science and 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, and it can provide a longer range under limited fuel conditions while reducing 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.]. An excellent airfoil design can obtain a high lift-to-drag ratio, effectively reduce fuel consumption, reduce carbon emissions, increase the range and endurance time, which is crucial for improving the flight efficiency and economy of the aircraft.

[0004] The key parameters of the airfoil directly affect the performance of the airfoil in terms of aerodynamics and drag reduction. For example, the thickness of the airfoil refers to the maximum distance perpendicular to the chord line between the upper and lower surfaces, which directly affects the drag and structural strength of the airfoil; the camber of the airfoil refers to the maximum distance between the mean camber line and the chord line, which affects the generation of lift; the trailing edge angle refers to the angle between the tangents of the upper and lower surfaces at the trailing edge point, which affects the air flow separation and control moment of the airfoil, etc. Small changes in these parameters will result in large differences in the lift and drag calculations. Therefore, in numerical calculations, it is necessary to restore the real airfoil design as much as possible, which involves the representation of the airfoil.

[0005] The actual airfoil is composed of curves or arcs and has a certain degree of curvature. In the numerical simulation method used in airfoil design, the physical space needs to be discretized into a computational space using grids, and the curve forming the airfoil serves as the "wall" boundary of the computational space. However, the structured grids, unstructured grids, or Cartesian grids commonly used in engineering applications are all composed of geometric shapes such as quadrilaterals, triangles, tetrahedrons, and hexahedrons. The curved boundary of the airfoil is treated as a straight line, or a certain numerical method is used to express and approximate the curved boundary. To a certain extent, this expression and approximation endow the wall boundary with certain curve properties, but the accuracy of the curved boundary expression determines the approximation degree between the numerical representation and the actual airfoil. The low-order curved boundary expression method cannot accurately represent the curved surface boundary of the aircraft, making it impossible for the numerical simulation to precisely reflect the actual airfoil shape. The tiny differences in the key parameters between the numerical simulation and the actual airfoil directly affect the calculation accuracy of the airfoil in aerodynamic calculations such as lift and drag, resulting in inaccurate numerical simulations and the inability to reflect the true performance of the airfoil.

[0006] Currently, the commonly used curved boundary expression methods include polynomial curves, cubic spline curves, and Bezier curves, etc. The design of polynomial curves is simple. Different-order polynomial expressions can be obtained through the known point information, and continuity can be achieved. In contrast, since the cubic spline curve simultaneously limits the values at the endpoints and the first and second derivative values, it can achieve Continuous. Li Ming [Li Ming, Research on High-Order DG / FV Hybrid Algorithm Based on Hybrid Grid, China Aerodynamics Research and Development Center, 2013.] adopted cubic spline curves to achieve high-order representation of curved boundaries for the Discontinuous Galerkin (DG) / Finite Volume (FV) scheme in his work. Different from polynomials and cubic spline curves, Bézier [Bézier, Numerical Control: Mathematics and Applications, McGraw-Hill, 1972.] curves are essentially a fitting method that usually only passes through the first and last control points. Gao, Wang [Gao H, Wang Z, Liu Y, A Study of Curved Boundary Representations for 2D High Order Euler Solvers. J Sci Comput, 2010, 44: 323–336.] and others adopted Bézier curves within the framework of the spectral volume scheme to achieve third-order representation of curved boundaries. For each element, in addition to the two end points on the curved boundary, two intermediate points need to be determined by the tangent vectors at the end points, and then a local Bézier curve representation is constructed. However, the implementation of this method requires the prior knowledge of the analytical expression of the curve, and it needs to be further improved for arbitrary curve configurations.

[0007] The piecewise idea can effectively improve the fitting degree between the standard cubic spline interpolation curve and the analytical curved surface, but there are still many limitations. First, the polynomial order of the cubic spline interpolation curve is fixed at the third order. If we want to further improve the curve representation order, we will face more complex derivations. Second, whether it is the standard or piecewise cubic spline interpolation method, artificial boundary conditions need to be given. The current mainstream treatment method is to impose natural boundary conditions on the starting and ending points of the curve. However, for different curve configurations, this artificial factor will lead to potential errors. Finally, although based on the piecewise idea, the constructed , and , continuous curve significantly reduces the geometric error of the interpolation curve, but at the junction points of segments, it will lead to an increase in error, and the realization of and continuity is premised on

[0008] If the above corresponding conditions cannot be met, the continuity cannot be guaranteed, and even calculation failures may occur. Summary of the Invention

[0009] The technical problem to be solved by the present invention is to provide a method for designing an aircraft wing, a terminal device and a storage medium, aiming at the deficiencies of the prior art, so that the wing boundary can more accurately fit the actual situation.

[0010] To solve the above technical problem, the technical solution adopted by the present invention is: a method for designing an aircraft wing, including the following steps: 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 according to the sorting result, and divide the wing boundary into n segments according to the adjacent relationship; S2. Judge whether the loop of the n segments of the wing boundary ends. If so, end; otherwise, construct a Vandermonde matrix for the i-th segment of the boundary curve; S3. Judge the polynomial degree of the i-th segment of the boundary curve. If it is cubic, normalize the Vandermonde matrix of the cubic polynomial. If it is quartic, normalize the Vandermonde matrix of the quartic polynomial. If it is quintic, normalize the Vandermonde matrix of the quintic polynomial; S4. Calculate the polynomial coefficients using the normalized Vandermonde matrix to determine the high-order polynomial curve of the i-th wing segment; S5. Increment the value of i by 1 and return to step S2.

[0011] In step S1, the specific implementation process of dividing the wing boundary into n segments according to the adjacent relationship includes: for the local part of the wing boundary, if the and show a size change, that is, from to , or from to , then segment at the changing position so that the points of and are on different segments; is the difference in the abscissa between the i-th reference point and the (i - 1)-th reference point, is the difference in the ordinate between the i-th reference point and the (i - 1)-th reference point.

[0012] For the quintic polynomial, the expression of the Vandermonde matrix is: ; For the quintic polynomial, the expression after normalizing the Vandermonde matrix is: ; Among them, is the normalized parameter in the x direction, , , , Respectively 2, 3, 4 and 5 times, ~ are the ordinates of the six reference points, and a~f are the unknown coefficients of the quintic polynomial.

[0013] 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.

[0014] 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.

[0015] As an inventive concept, the present invention also provides a computer program product, including a computer program / instruction; when the computer program / instruction is executed by a processor, the steps of the above method are implemented.

[0016] Compared with the prior art, the present invention has the following beneficial effects: 1. Since the airfoil should be curved, but after mesh discretization, it is composed of line segments, 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 flying; 2. In the prior art, in the mesh drawing stage, the boundary of the irregular curve is directly replaced by a line segment, which inevitably results in an approximate error, resulting in inaccurate design using line segments directly. The estimated result is not the result of the real airfoil, but the result of an approximate airfoil composed of line segments. By adopting the method of the present invention, the curve is restored starting from the line segment, the shape of the airfoil is restored, and the error between the calculated shape and the actual shape is effectively reduced, thereby greatly improving the accuracy of the computational simulation. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a quadrilateral mesh NACA0012 airfoil; Figure 2 A schematic diagram of the reference point selection method for expressing polynomial curves of different degrees; Figure 3 The overall situation of three polynomial interpolation curves under different reference point distributions; (a) 80 reference points, (b) 140 reference points; Figure 4 Local conditions of three polynomial interpolation curves under different reference point distributions; (a) 80 reference points, (b) 140 reference points; Figure 5 Geometric error distributions of polynomials and cubic spline interpolation curves under different reference point distributions; (a) 80 reference points, (b) 140 reference points; Figure 6 Schematic diagram of the relative position relationship of normalized parameter points of polynomials from degree three to five; Figure 7 Condition numbers and the reduction multiples of condition numbers before and after the planning of Vandermonde matrices of polynomials from degree three to five; (a) Cubic polynomial, (b) Quartic polynomial, (c) Quintic polynomial, (d) Reduction multiple of condition number; Figure 8 Flowchart of the method of the embodiment of the present invention; Figure 9 Comparison of the effects before and after the improvement of polynomial interpolation curves under different reference point distributions; (a) 80 reference points, (b) 140 reference points; Figure 10 Geometric error distributions of polynomial interpolation curves before and after improvement under different reference point distributions; (a) 80 reference points, (b) 140 reference points; Figure 11 Performance of improved cubic spline curves and polynomial curves near different positions; (a) Position 1, (b) Position 2, (c) Position 3, (d) Position 4; Figure 12 Fitting conditions of improved cubic spline and polynomial curves at different positions of the NACA0012 airfoil; (a) Overall curve, (b) Local position 1, (c) Local position 2, (d) Local position 3. Specific implementation manners

[0018] To make the objectives, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are some, but not all, of the embodiments of the present invention. All other embodiments obtained by those of ordinary skill in the art without creative efforts based on the embodiments of the present invention belong to the scope of protection of the present invention.

[0019] Embodiment 1

[0020] The expression of the airfoil curve boundary requires using a curve function to represent the geometric model boundary of the airfoil, which involves the mapping from the geometric model to the computational model.

[0021] The mapping of the geometric model to the computational model requires three steps: generating a mesh, constructing a coordinate system, and calculating coordinates. Taking the NACA0012 airfoil shown in Figure 1 as an example, the three steps will be described below.

[0022] 1. Generating a mesh As shown in Figure 1 , first, points are densely distributed on the boundary of the geometric model of the NACA0012 airfoil for the discretization of the geometric boundary. These points are called grid points, and the adjacent grid points are connected to form grid edges. After the grid edges on the geometric boundary are formed, a grid generation software can be used to generate a mesh for the external computational domain of the NACA0012 airfoil. As shown in Figure 1 , a quadrilateral mesh can be generated, or a triangular mesh can also be generated. The grid edges in the computational model are straight line segments, while the airfoil boundary in the geometric model is a curved line segment. Therefore, the mesh cannot directly coincide with the curved boundary.

[0023] 2. Constructing a coordinate system It is necessary to construct the XOY plane. Set the leading-edge point of the NACA0012 airfoil as point O. Along the chord line of the NACA0012 airfoil, that is, the straight line connecting the leading edge and the trailing edge, set the x-axis, and the direction from the leading edge to the trailing edge is the positive direction of the x-axis. Pass through point O and set the direction perpendicular to the x-axis as the y-axis, and the upward direction is the positive direction of the y-axis.

[0024] 3. Calculating coordinates For each grid point in the computational model, calculate the grid coordinates of the grid point in the XOY plane according to the grid scale . Since the grid points strictly fall on the geometric boundary, the coordinates of the grid points are accurate. For the coordinates on other geometric boundaries except the grid points, approximate values need to be obtained through the curved boundary expression function.

[0025] After completing the above three steps, the curved boundary expression function can be constructed by numerical methods.

[0026] The process of curved boundary expression requires constructing a curved boundary expression function. Given the grid point coordinates and that strictly fall on the geometric boundary, and these two grid points are adjacent, then the curved boundary expression function can be constructed. can approximately obtain and the coordinates of any point on the curved boundary between the two grid points, where . Obtaining all the expressions, the curved boundary can be completely expressed.

[0027] Taking And Take the curved boundary between them as an example to illustrate the construction method of the standard polynomial function The standard cubic, quartic, and quintic polynomial forms can be expressed as follows respectively: ; The polynomials of the three orders contain 4, 5, and 6 unknowns respectively. Therefore, for the polynomial expression of each local surface, the corresponding number of reference points is required. Figure 2 The parameter point selection methods adopted in the embodiments of the present invention under three conditions are respectively shown in

[0028] On this basis, it is necessary to solve the undetermined coefficients of the polynomial. Taking the quintic polynomial as an example, assuming that the six reference points are respectively to , the following Vandermonde equations can be obtained: ; This system is a system of equations with definite solutions. The embodiments of the present invention adopt the SVD method to calculate the matrix inverse, and then obtain the polynomial coefficients.

[0029] The curve expression effects of polynomials of three different orders are respectively shown below. As Figure 3 shown, overall, smooth cylindrical surface curves can be obtained based on the three polynomials. However, from the local enlarged views of the left and right end points shown in Figure 4 , it can be seen that obvious errors are shown near the end points for the cubic to quintic polynomials, and the errors gradually increase as the polynomial degree increases.

[0030] To quantitatively show the geometric error situation of the polynomial interpolation curve at different positions, Figure 5 the error distributions of the three polynomial curves and the standard cubic spline curve for the upper surface of the cylinder are statistically analyzed in

[0031] It can be seen that whether it is polynomial interpolation or the standard cubic spline interpolation curve, the geometric errors are relatively high near the left and right end points of the cylinder, and the errors in the middle part are lower. In addition, as the polynomial degree continues to increase, the geometric error in the middle part gradually decreases. The geometric error of the cubic spline interpolation curve is between the cubic and quartic polynomial curves, but significantly higher than that of the quintic polynomial curve.

[0032] The advantages of the embodiments of the present invention are illustrated by experimental data below.

[0033] The improved piecewise high-degree polynomial method includes segmenting the airfoil curve and normalizing the solution of the Vandermonde matrix. Through these two steps, the calculation error of the standard polynomial method at the extreme positions of the airfoil curve can be reduced.

[0034] Although the implementation of the polynomial interpolation curve is simple and it is easy to extend to quartic and quintic, at extreme positions where the sensitivity to the x - coordinate is high, such as near the left and right endpoints of a cylinder, for cubic, quartic, or quintic polynomials, there will be a relatively high geometric error in the reconstructed curve.

[0035] The improved high - degree polynomial method will adopt a piece - wise idea and perform piece - wise processing on a standard curve. The specific piece - wise method is to compare the relationship between and locally on the curve. If the and between adjacent reference points change in magnitude, that is, from to , or from to , then segment at the changing position so that the points of and are on different segments. After segmentation, the specific form of the curve polynomial can be determined. Note that the polynomial interpolation curve does not require any artificial conditions, so no complex processing is needed between segments.

[0036] Improved Vandermonde matrix normalization strategy: From the Vandermonde equation system, solving for the undetermined coefficients of the polynomial requires calculating the inverse of the Vandermonde matrix. However, in practical situations, this matrix often has an overly large condition number. Taking the quintic polynomial curve as an example, assume that the positions of the six required parameter points are at relatively extreme positions on the leading edge of an airfoil, which are

[0037] At this time, the local Vandermonde system with 6 significant figures retained can be expressed as ; It can be seen that as the power exponent of the terms in 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. But if reasonable normalization parameters are selected for the Vandermonde matrix, and starting from the second column of the matrix, all column elements are normalized respectively with , , , and , the new Vandermonde system can be expressed as ; In the embodiments of the present invention, the expressions of the normalized third- and fourth-order Vandermonde matrices are based on the fifth-order Vandermonde matrix, with the last column and the last row deleted; or the last two columns and the last two rows deleted.

[0038] Based on this idea, the parameters selected for the third- to fifth-order polynomial curves or The positional relationship is as Figure 6 shown. In the figure, the black dots represent the position points where the normalized parameters are located.

[0039] Taking the upper surface curve (circular boundary) of a cylinder with 140 reference points on the surface distribution as an example, Figure 7 shows the condition number of the Vandermonde matrix corresponding to each small segment of the polynomial curve before and after normalization, and the multiple by which the condition number decreases after optimization.

[0040] From Figure 7 the results shown, it can be seen that whether it is a third-, fourth- or fifth-order polynomial, based on the given Vandermonde matrix normalization scheme, the condition number of the matrix will be significantly reduced by 2 to 3 orders of magnitude. This will help improve the stability of the SVD method for solving the matrix inverse, reduce the inversion error, and improve the accuracy of polynomial coefficient solution.

[0041] The method flow of this embodiment is as Figure 8 shown.

[0042] As Figure 8 shown, the improved piecewise high-order polynomial method is divided into the following key steps: 1. Read the coordinates of the airfoil boundary grid points ; 2. Arrange the grid point coordinates in ascending order of x first; 3. Determine the adjacent relationship between the grid points on the airfoil boundary according to the sorting, and divide the airfoil curve into n segments according to the relationship between ; 4. Loop through each of the n segments, determine whether the loop ends. If not, go to 5; if it ends, go to; 5. Construct the Vandermonde matrix of the i-th segment curve; 6. Determine the polynomial degree. If it is to construct a third-order polynomial curve, go to 7; if it is to construct a third-order polynomial curve, go to 8; if it is to construct a third-order polynomial curve, go to 9; 7. Normalize the Vandermonde matrix of the third-order polynomial curve and go to 10; 8. Normalize the Vandermonde matrix of the quartic polynomial curve, and go to 10; 9. Normalize the Vandermonde matrix of the quintic polynomial curve, and go to 10; 10. Use the SVD method to solve the normalized Vandermonde matrix of the high-degree polynomial curve, obtain the airfoil curve expression on the i-th segment, and go to 4; 11. End.

[0043] Figure 9 First, the fitting situation between the polynomial interpolation curve and the analytical curve near the left and right endpoints of the curve on the upper surface of the cylinder (circular boundary) before and after improvement is shown.

[0044] From Figure 9 It can be seen that whether there are 80 or 140 reference points distributed on the cylinder surface, after improvement based on the segmented idea, the fitting situation between the cubic to quintic polynomial curves and the cylinder analytical curve is ideal, and there are no obvious deviations at the left and right endpoints, showing obvious improvement compared with the standard polynomial curve. From Figure 10 The geometric error distribution on the upper surface of the cylinder shown in it can more clearly show this point. The error of the improved multi-form interpolation curve at the left and right endpoints is significantly reduced, and at the boundary points between segments, the situation where the geometric error of the improved cubic spline interpolation curve is higher than that of the curve before improvement does not occur.

[0045] Judging from the obtained results, reconstructing the curved surface expression based on the polynomial interpolation curve is a relatively ideal strategy. After improving it in a segmented manner, the fitting situation with the analytical surface can be effectively improved.

[0046] After improving the polynomial curve based on the segmented expression and matrix normalization ideas, the fitting degree between the reconstructed curve and the analytical curve is significantly improved, and the geometric error is reduced.

[0047] Figure 11 Shows the performance of the improved cubic spline and polynomial curves at four different positions when there are 140 reference points distributed on the cylinder surface.

[0048] Judging from the results, at the four positions, the fitting situations of the two improved cubic spline curves with the analytical cylinder curve are not ideal. In contrast, the polynomial curves, especially the quintic polynomial curve, are very close to the cylinder surface near the four positions shown.

[0049] In the embodiment of the present invention, based on the cylinder curve, the real airfoil - NACA0012 airfoil in engineering applications is further considered. The curves on the upper and lower surfaces of this airfoil have analytical expressions .

[0050] The following will continue to show the improved curve expression effects at different positions.

[0051] From Figure 12 It can be seen that for the NACA0012 airfoil, the relative error between the improved polynomial curve and the analytical curve is lower than that of the cubic spline curve near the displayed positions. Therefore, the two typical shapes prove the advantages of the improved polynomial curve compared to the cubic spline curve. In particular, the fifth-degree polynomial curve has a lower geometric error and a higher fitting degree with the analytical curve, providing a prerequisite for the implementation of high-order formats on curved elements. At the same time, the higher fitting degree with the analytical curve can also largely overcome the situation where the reconstructed curve passes through the first few layers of grids in high Reynolds number flows.

[0052] Embodiment 2

[0053] Embodiment 2 of the present invention provides a measurement system corresponding to Embodiment 1 above. The measurement system can be a processing device for a client, such as a mobile phone, a laptop computer, a tablet computer, a desktop computer, etc., to execute the method of the above embodiment.

[0054] The measurement system of this embodiment includes a memory, a processor, and a computer program stored on the memory; the processor executes the computer program on the memory to implement the steps of the method of Embodiment 1 above.

[0055] In some implementations, the memory can be a high-speed random access memory (RAM: Random Access Memory), and may also include non-volatile memory, such as at least one disk memory.

[0056] In other implementations, the processor can be various types of general-purpose processors such as a central processing unit (CPU), a digital signal processor (DSP), etc., which are not limited here.

[0057] Although the preferred embodiments of the present application have been described, those skilled in the art can make additional changes and modifications to these embodiments once they know the basic creative concept. Therefore, the appended claims are intended to be interpreted to include the preferred embodiments as well as all changes and modifications falling within the scope of the present application.

[0058] Obviously, those skilled in the art can make various changes and modifications to the present application without departing from the spirit and scope of the present application. Thus, if these modifications and variations of the present application fall within the scope of the claims of the present application and their equivalent technologies, the present application also intends to include these changes and modifications.

Claims

1. A method for designing an aircraft wing, characterized in that, Including the following steps: S1. Obtain the wing boundary grid point coordinates, sort the grid point coordinates, determine the adjacent relationship between the grid points on the wing boundary according to the sorting result, and divide the wing boundary into n segments according to the adjacent relationship; S2. Judge whether the loop of the n segments of the wing boundary ends. If so, end; otherwise, construct a Vandermonde matrix for the i-th segment of the boundary curve; S3. Judge the polynomial degree of the i-th segment of the 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 the polynomial coefficients using the normalized Vandermonde matrix to determine the high-order polynomial curve of the i-th segment of the wing; S5. Increment the value of i by 1 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 local wing boundary, if there is a change in the magnitude between adjacent reference points and appears, that is, from changes to , or from changes to , then segmentation is performed at the changing position so that and points are on different segments; is the difference in the abscissa between the i-th reference point and the (i - 1)-th reference point, is the difference in the ordinate between the i-th reference point and the (i - 1)-th reference point.

3. The aircraft wing design method according to claim 1, wherein, For a fifth-degree polynomial, the Vandermonde matrix has the following expression: 。 4. The aircraft wing design method according to claim 1, wherein For the quintic polynomial, the expression after normalizing the Vandermonde matrix is: ； Among them, is the normalization parameter in the x direction, , , , respectively represent the second, third, fourth, and fifth powers of ~ are the ordinates of six reference points, and a to f are the undetermined coefficients of the fifth-degree polynomial.

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

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

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

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