Rapid modeling and simulation method and system for deformed wing structure

Abstract

The invention relates to the technical field of computer simulation, and discloses a rapid modeling simulation method and system for a deformed wing structure, and the method comprises the steps: recognizing wing section key points of wing section data, fitting an upper surface curve and a lower surface curve of the deformed wing structure, and determining a parameterized wing section of the deformed wing structure; analyzing key change parameters, corresponding to the wingspan direction, of the deformed wing structure so as to construct a parameter change curve in the wingspan direction, and fitting a wing geometric model of the deformed wing structure; determining a deformation mode of the deformed wing structure, calculating an airfoil variable quantity and a torsion angle variable quantity of the deformed wing structure in a deformation process, and fitting an initial deformed wing model of the deformed wing structure; carrying out simulation calculation on an aerodynamic coefficient of the initial deformation wing model, and determining aerodynamic performance of the initial deformation wing model; and optimizing the initial deformation wing model to obtain a target deformation wing model. According to the method, the modeling simulation accuracy and design efficiency of the deformed wing structure can be improved.

Description

Technical Field

[0001] This invention relates to a rapid modeling and simulation method and system for deformable wing structures, belonging to the field of computer simulation technology. Background Technology

[0002] Rapid modeling and simulation of morphing wing structures refers to a method specifically designed for wing structures capable of altering their shape (e.g., by changing airfoil, twist angle, spanwise shape). This method enables the rapid completion of geometric modeling, physical model establishment, and subsequent performance (primarily aerodynamic and structural mechanical properties) simulation. Rapid modeling and simulation of morphing wing structures can efficiently evaluate the impact of different deformation strategies on various aspects of an aircraft's performance, including aerodynamic efficiency, structural efficiency, handling, and stability, helping to design aircraft that truly leverage the advantages of deformation to achieve performance leaps.

[0003] Traditional morphing wing structure modeling involves constructing geometric models using complex methods such as NURBS and B-splines. This method requires defining a large number of control points, weights, and node vectors to build a complete wing geometry model. Every detail needs to be carefully adjusted, making the process cumbersome and difficult to control precisely. It is also difficult to control complex geometric shapes and deformation patterns accurately and quickly. Summary of the Invention

[0004] This invention provides a rapid modeling and simulation method and system for deformable wing structures, the main purpose of which is to improve the accuracy and design efficiency of deformable wing structure modeling and simulation.

[0005] To achieve the above objectives, the present invention provides a rapid modeling and simulation method for deformable wing structures, comprising: Collect wing section data of deformable wing structure, identify key points of wing section data, wherein the key points of wing section include: leading edge point, trailing edge point and maximum thickness point, fit the upper surface curve and lower surface curve of deformable wing structure according to the key points of wing section, and combine the upper surface curve and lower surface curve to determine the parameterized wing section of deformable wing structure; The key variation parameters of the deformable wing structure in the span direction are analyzed, including the sweep angle, dihedral angle, and twist angle, to construct the parameter variation curve in the span direction. The wing geometric model of the deformable wing structure is then fitted by combining the parameter variation curve and the parameterized wing section. The deformation mode of the deformable wing structure is determined. Based on the deformation mode, the airfoil change and the torsion angle change of the deformable wing structure during the deformation process are calculated. Combining the wing geometric model, the airfoil change, and the torsion angle change, an initial deformable wing model of the deformable wing structure is fitted. The simulation environment of the initial deformable wing model is determined to simulate and calculate the aerodynamic coefficients of the initial deformable wing model. Based on the aerodynamic coefficients, the aerodynamic performance of the initial deformable wing model is determined. Based on the aerodynamic performance, the initial deformable wing model is optimized to obtain the target deformable wing model.

[0006] Optionally, fitting the upper and lower surface curves of the deformable wing structure based on the key points of the wing section includes: Based on the key points of the wing section, calculate the chord length and maximum thickness of the deformable wing structure; The deformable wing structure is divided into a leading edge section, a middle section, and a trailing edge section; Polynomial fitting is performed on the leading edge interval, the middle section interval, and the trailing edge interval respectively to obtain the upper and lower surface curves of the leading edge, the upper and lower surface curves of the middle section, and the upper and lower surface curves of the trailing edge. Define the constraint conditions at the boundary between the leading edge interval, the middle section interval, and the trailing edge interval; Based on the boundary constraint conditions, the upper and lower surface curves of the leading edge, the upper and lower surface curves of the middle section, and the upper and lower surface curves of the trailing edge are spliced ​​together to obtain the spliced ​​upper surface curve and the spliced ​​lower surface curve. Determine the upper surface curve error term and the lower surface curve error term of the spliced ​​upper surface curve and the spliced ​​lower surface curve; Based on the error terms of the upper surface curve and the lower surface curve, the spliced ​​upper surface curve and the spliced ​​lower surface curve are smoothed to obtain the upper surface curve and the lower surface curve.

[0007] Optionally, the analysis of key variation parameters of the deformable wing structure in the span direction includes: Identify the leading edge line of the deformable wing structure and analyze the offset of the leading edge line from the leading edge line in the chord direction of the corresponding wing structure. Determine the wingspan increment in the wingspan direction, and calculate the sweep angle of the deformable wing structure based on the wingspan increment and the leading edge offset; Measure the vertical offset of the leading edge point of the deformable wing structure, and calculate the dihedral angle of the deformable wing structure based on the vertical offset and the wingspan increment; Determine the root chord vector of the deformable wing structure, and calculate the torsion angle of the deformable wing structure based on the root chord vector and the reference baseline vector; Based on the sweep angle, the dihedral angle, and the torsion angle, the key variation parameters of the deformable wing structure corresponding to the wingspan direction are determined.

[0008] Optionally, fitting the wing geometry model of the deformable wing structure by combining the parameter variation curve and the parameterized wing section includes: Discretize the wingspan direction of the deformable wing structure to obtain the discretized wingspan position; Extract the discretized parameters corresponding to the discretized wingspan position from the parameter variation curve; Based on the discretization parameters, determine the rotation matrix of the discretized wingspan position; Based on the parameterized wing section, calculate the airfoil parameters corresponding to the discretized wingspan position; Based on the airfoil parameters and the rotation matrix, the parameterized wing section corresponding to the discretized wingspan position is fitted with a surface to obtain the initial wing geometric model; The model quality of the initial wing geometry model is detected. When the model quality meets the preset model quality standard, the initial wing geometry model is used as the wing geometry model of the deformable wing structure.

[0009] Optionally, calculating the airfoil change and twist angle change of the deformable wing structure during the deformation process based on the deformation mode includes: Extract the torsional modal coefficients of the deformation mode; Analyze the torsional deformation function in the deformation mode; Based on the torsional modal coefficients and the torsional deformation function, the change in torsional angle of the deformable wing structure during the deformation process is calculated; Extract the thickness variation coefficient and curvature variation coefficient of the deformation mode; The thickness change of the deformable wing structure is calculated based on the thickness change coefficient. The camber change of the deformable wing structure is calculated based on the camber change coefficient. Based on the thickness change and the camber change, the airfoil change during the deformation process of the deformable wing structure is determined.

[0010] Optionally, the step of fitting the initial deformable wing model of the deformable wing structure by combining the wing geometry model, the airfoil variation, and the twist angle variation includes: The wing geometry model is meshed to obtain a three-dimensional wing surface mesh, wherein the three-dimensional wing surface mesh includes: ; in, This represents the mesh coordinates of the 3D wing surface mesh when the wing geometry is undeformed. Coordinates representing the wingspan direction, Represents chord coordinates, Represents the coordinates in the wingspan direction Initial distribution of the twist angle at the position, Represents the coordinates in the chord direction Initial thickness distribution at location, Represents the sine function. Represents the cosine function; Determine the initial coordinates of the grid points of the three-dimensional wing surface mesh; Based on the airfoil change and the twist angle change, the initial coordinates of the grid points are updated to obtain the updated airfoil coordinates. Based on the updated airfoil coordinates, the initial deformable wing model of the deformable wing structure is fitted.

[0011] Optionally, the simulation calculation of the aerodynamic coefficients of the initial deformable wing model includes: Determine the free flow velocity of the simulation environment corresponding to the initial deformable wing model; Calculate the dynamic pressure provided by the simulation environment based on the free flow velocity; The lift, drag, and pitching moment of the initial deformable wing model in the simulation environment were detected. Based on the dynamic pressure, lift, drag, and pitching moment, the lift coefficient, drag coefficient, and pitching moment coefficient of the initial deformable wing model are calculated using the following formulas: ; ; ; in, Indicates the lift coefficient. Indicates the drag coefficient. Indicates the pitching moment coefficient. Indicates lift. Indicates dynamic pressure. This represents the projected area of ​​the initial deformable wing model. Indicates resistance. Indicates pitching moment, c represents the wingspan of the initial deformable wing model. Indicates position in the wingspan direction String length, Indicates position Integrate points; The aerodynamic coefficients of the initial deformable wing model are determined based on the lift coefficient, the drag coefficient, and the pitching moment coefficient.

[0012] Optionally, determining the aerodynamic performance of the initial deformable wing model based on the aerodynamic coefficients includes: Indeed, the test elevation angle of the initial deformable wing model was determined; Construct the coefficient-angle curves for the aerodynamic coefficients and the test elevation angle; Identify the stall angle of attack, drag variation state, and pitching moment characteristics of the coefficient-angle curve; The aerodynamic performance of the initial deformable wing model is determined based on the stall angle of attack, the drag variation state, and the pitching moment characteristics.

[0013] Optionally, optimizing the initial deformable wing model based on the aerodynamic performance to obtain the target deformable wing model includes: Determine whether the aerodynamic performance meets the preset aerodynamic performance standard; When the aerodynamic performance does not meet the aerodynamic performance standard, identify the influence parameters of the initial deformable wing model; Based on the influencing parameters, the initial deformable wing model is optimized to obtain the optimized deformable wing model; Calculate the optimized aerodynamic coefficients of the optimized deformable wing model to analyze its optimized aerodynamic performance; When the optimized aerodynamic performance meets the aerodynamic performance standard, the optimized deformable wing model is used as the target deformable wing model.

[0014] To address the above problems, the present invention also provides a rapid modeling and simulation system for deformable wing structures, the system comprising: The parametric wing section module is used to collect wing section data of deformable wing structures and identify key points of the wing section data. The key points of the wing section include: leading edge point, trailing edge point, and maximum thickness point. Based on the key points of the wing section, the upper surface curve and lower surface curve of the deformable wing structure are fitted. Combining the upper surface curve and lower surface curve, the parametric wing section of the deformable wing structure is determined. The wing geometry model construction module is used to analyze the key variation parameters of the deformable wing structure in the wingspan direction. The key variation parameters include: sweep angle, dihedral angle and twist angle, so as to construct the parameter variation curve in the wingspan direction. Combining the parameter variation curve and the parameterized wing section, the wing geometry model of the deformable wing structure is fitted. The deformable wing model construction module is used to determine the deformation mode of the deformable wing structure, calculate the airfoil change and twist angle change of the deformable wing structure during the deformation process based on the deformation mode, and fit the initial deformable wing model of the deformable wing structure by combining the wing geometric model, the airfoil change and the twist angle change. The aerodynamic performance analysis module is used to determine the simulation environment of the initial deformable wing model, to simulate and calculate the aerodynamic coefficients of the initial deformable wing model, and to determine the aerodynamic performance of the initial deformable wing model based on the aerodynamic coefficients. The target deformable wing model module is used to optimize the initial deformable wing model based on the aerodynamic performance to obtain the target deformable wing model.

[0015] Compared to the problems described in the background art, the embodiments of the present invention, by fitting the upper and lower surface curves of the deformable wing structure based on the key points of the wing section, can transform the geometric data of the deformable wing from a discrete set of points into a computable and optimizable continuous model, laying the foundation for subsequent simulation, control, and manufacturing. Optionally, by combining the upper and lower surface curves, the embodiments of the present invention determine that the parameterized wing section of the deformable wing structure can accurately reconstruct the geometry of the original wing section through precise fitting of the upper and lower surface curves. Furthermore, by combining the parameter variation curves and the parameterized wing section, the embodiments of the present invention can fit a wing geometric model of the deformable wing structure that reflects both real deformation and structure, providing a reliable foundation for subsequent multidisciplinary analysis in aerodynamics, structure, and control, thereby enabling a more comprehensive understanding and evaluation of deformable wings. The invention provides a method and system for rapid modeling and simulation of deformable wing structures. By combining the wing geometry model, airfoil variation, and torsion angle variation, the initial deformable wing model of the deformable wing structure can be fitted to accurately and visually represent the geometric characteristics of the deformable wing, providing reliable basic data and model support for subsequent aerodynamic, structural, and control research and design. Furthermore, by determining the aerodynamic performance of the initial deformable wing model based on the aerodynamic coefficients, the invention can evaluate the effects of specific deformation modes (such as changing camber and torsion angle) on improving lift, reducing drag, and enhancing stability and maneuverability. Finally, by optimizing the initial deformable wing model based on the aerodynamic performance, the invention obtains a target deformable wing model that improves multiple key aerodynamic characteristics such as lift, drag, stability, and maneuverability, ultimately resulting in a high-quality deformable wing model. Therefore, the rapid modeling and simulation method and system for deformable wing structures provided by this invention can improve the accuracy and design efficiency of deformable wing structure modeling and simulation. Attached Figure Description

[0016] Figure 1This is a flowchart illustrating a rapid modeling and simulation method for deformable wing structures provided in an embodiment of the present invention. Figure 2 This is a schematic diagram of a module for implementing the rapid modeling and simulation method for deformable wing structures according to an embodiment of the present invention.

[0017] The objectives, features, and advantages of this invention will be further explained in conjunction with the embodiments and with reference to the accompanying drawings. Detailed Implementation

[0018] It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.

[0019] This application provides a rapid modeling and simulation method for deformable wing structures. The execution entity of this rapid modeling and simulation method includes, but is not limited to, at least one of the following electronic devices that can be configured to execute the method provided in this application: a server, a terminal, etc. In other words, the rapid modeling and simulation method for deformable wing structures can be executed by software or hardware installed on a terminal device or a server device. The server includes, but is not limited to, a single server, a server cluster, a cloud server, or a cloud server cluster.

[0020] Example 1: Reference Figure 1 The diagram shown is a flowchart illustrating a rapid modeling and simulation method for deformable wing structures according to an embodiment of the present invention. In this embodiment, the rapid modeling and simulation method for deformable wing structures includes: S1. Collect wing section data of the deformable wing structure, identify key points of the wing section data, wherein the key points of the wing section include: leading edge point, trailing edge point and maximum thickness point, fit the upper surface curve and lower surface curve of the deformable wing structure according to the key points of the wing section, and combine the upper surface curve and the lower surface curve to determine the parameterized wing section of the deformable wing structure.

[0021] This invention, through the acquisition of wing cross-sectional data of a deformable wing structure, can accurately locate the leading edge, trailing edge, and maximum thickness point, fit the curves of the upper and lower surfaces, and faithfully reconstruct the three-dimensional geometry of the wing cross-section, supporting subsequent model construction. The wing cross-sectional data refers to a set of information on the geometry and position of a specific cross-section of the wing.

[0022] Optionally, the wing cross-sectional data of the deformable wing structure can be acquired using optical measurement techniques, such as laser scanners, photogrammetry, and stereo vision.

[0023] This invention, through the identification of key points in the wing cross-section data, can serve as control nodes for a parametric model, reducing data volume and improving modeling efficiency. The key points of the wing cross-section refer to several critical locations on a certain cross-section of the wing that have specific geometric or aerodynamic significance. The leading edge point is the point at the very front of the wing's cross-section. The trailing edge point is the point at the very back of the wing's cross-section. The maximum thickness point is the point on the wing's cross-section where the distance perpendicular to the chord direction reaches its maximum.

[0024] This invention, through fitting the upper and lower surface curves of the deformable wing structure based on key points of the wing cross-section, transforms the geometric data of the deformable wing from a discrete point set into a computable and optimizable continuous model, laying the foundation for subsequent simulation, control, and manufacturing. The upper surface curve refers to the curve constituting the upper half of the airfoil's cross-sectional profile. The lower surface curve refers to the curve constituting the lower half of the airfoil's profile on the wing's cross-section.

[0025] As an embodiment of the present invention, the step of fitting the upper surface curve and lower surface curve of the deformable wing structure based on the key points of the wing section includes: Based on the key points of the wing section, calculate the chord length and maximum thickness of the deformable wing structure; The deformable wing structure is divided into a leading edge section, a middle section, and a trailing edge section; Polynomial fitting is performed on the leading edge interval, the middle section interval, and the trailing edge interval respectively to obtain the upper and lower surface curves of the leading edge, the upper and lower surface curves of the middle section, and the upper and lower surface curves of the trailing edge. Define the constraint conditions at the boundary between the leading edge interval, the middle section interval, and the trailing edge interval; Based on the boundary constraint conditions, the upper and lower surface curves of the leading edge, the upper and lower surface curves of the middle section, and the upper and lower surface curves of the trailing edge are spliced ​​together to obtain the spliced ​​upper surface curve and the spliced ​​lower surface curve. Determine the upper surface curve error term and the lower surface curve error term of the spliced ​​upper surface curve and the spliced ​​lower surface curve; Based on the error terms of the upper surface curve and the lower surface curve, the spliced ​​upper surface curve and the spliced ​​lower surface curve are smoothed to obtain the upper surface curve and the lower surface curve.

[0026] The chord length refers to the straight-line distance from the leading edge to the trailing edge on the wing cross-section. The maximum thickness value refers to the maximum distance on the wing cross-section perpendicular to the chord direction. The leading edge region refers to the area near the leading edge point on the wing cross-section. The mid-section region refers to the middle part of the wing cross-section located between the leading edge region and the trailing edge region. The trailing edge region refers to the area near the trailing edge point on the wing cross-section. The leading edge upper and lower surface curves refer to the upper and lower surface curves within the leading edge region on the wing cross-section. The mid-section upper and lower surface curves refer to the upper and lower surface curves of the region between the leading edge region and the trailing edge region on the wing cross-section. The trailing edge upper and lower surface curves refer to the upper and lower surface curves within the trailing edge region on the wing cross-section. The boundary constraint conditions refer to the specific requirements imposed at the connection points of the curves (the connection points of the leading edge region, mid-section, and trailing edge regions), such as positional continuity, tangent continuity, curvature continuity, etc. The spliced ​​upper surface curve refers to connecting and combining the segmented curves of the leading edge, middle section, and trailing edge sections according to the boundary constraints to form a complete, continuous, and smooth upper surface curve. The spliced ​​lower surface curve refers to connecting and combining the segmented curves of the leading edge, middle section, and trailing edge sections according to the boundary constraints to form a complete, continuous, and smooth lower surface curve. The upper surface curve error term is a measure of the degree of difference between the fitted spliced ​​upper surface curve and the wing section data points. The lower surface curve error term is a measure of the degree of difference between the fitted spliced ​​lower surface curve and the wing section data points.

[0027] Optionally, the boundary conditions between the leading edge interval, the middle interval, and the trailing edge interval can be defined by geometric continuity constraints, which include positional continuity, slope continuity, and curvature continuity.

[0028] Optionally, the leading edge upper and lower surface curves can be fitted by fitting a polynomial curve equation of the leading edge interval, calculating the polynomial coefficients of the polynomial curve equation using the least squares method, and fitting the leading edge upper and lower surface curves of the leading edge interval based on the polynomial coefficients.

[0029] Optionally, the upper surface curve error term of the spliced ​​upper surface curve can be determined by calculating the maximum error, root mean square error, and mean absolute error of the spliced ​​upper surface curve and the wing section data, and based on the maximum error, the root mean square error, and the mean absolute error.

[0030] This invention, by combining the upper and lower surface curves, determines that the parameterized wing section of the deformable wing structure can accurately reconstruct the geometry of the original wing section through precise fitting of the upper and lower surface curves. The parameterized wing section refers to a mathematical model that defines and controls the geometry of the wing cross-section using a set of adjustable parameters.

[0031] Optionally, the parameterized wing section of the deformable wing structure can be determined by lofting techniques, such as generating a transition surface between the upper surface curve and the lower surface curve, connecting the upper surface curve, the lower surface curve, and the transition surface into a closed surface using the lofting technique, and smoothing the closed surface to obtain the parameterized wing section.

[0032] S2. Analyze the key variation parameters of the deformable wing structure in the span direction, wherein the key variation parameters include: sweep angle, dihedral angle and twist angle, to construct the parameter variation curve in the span direction, and combine the parameter variation curve and the parameterized wing section to fit the wing geometric model of the deformable wing structure.

[0033] This invention, through analyzing key variation parameters of the deformable wing structure along its span, determines the angular changes in the span direction, thus providing a data foundation for subsequent 3D modeling. These key variation parameters refer to the main geometric parameters that significantly affect the overall wing geometry, aerodynamic performance, and flight characteristics, and which change along the span direction (from wing root to wingtip). The sweep angle is the angle between the wing leading edge line and a plane perpendicular to the fuselage axis (or plane of symmetry). The angle between the wing plane and the horizontal plane is also specified. The twist angle is the angle between the wing chord line of the wing section and a reference plane (such as the plane containing the wing root chord line).

[0034] As an embodiment of the present invention, the analysis of the key variation parameters of the deformable wing structure in the wingspan direction includes: Identify the leading edge line of the deformable wing structure and analyze the offset of the leading edge line from the leading edge line in the chord direction of the corresponding wing structure. Determine the wingspan increment in the wingspan direction, and calculate the sweep angle of the deformable wing structure based on the wingspan increment and the leading edge offset; Measure the vertical offset of the leading edge point of the deformable wing structure, and calculate the dihedral angle of the deformable wing structure based on the vertical offset and the wingspan increment; Define a reference baseline for the deformable wing structure and calculate the reference baseline vector of the reference baseline; Determine the root chord vector of the deformable wing structure, and calculate the torsion angle of the deformable wing structure based on the root chord vector and the reference baseline vector; Based on the sweep angle, the dihedral angle, and the torsion angle, the key variation parameters of the deformable wing structure corresponding to the wingspan direction are determined.

[0035] The leading edge line refers to the continuous curve formed by the leading edge edge of the wing. The leading edge line offset refers to the displacement of the leading edge line along the wing chord direction in the deformable wing structure. The vertical offset refers to the vertical displacement of the leading edge point in the deformable wing structure. The reference baseline refers to a pre-defined line used as a reference, such as the fuselage centerline or design baseline. The reference baseline vector refers to the representation of the reference baseline in vector space. The wing root chord vector refers to the vector defined by the chord at the wing root of the deformable wing structure.

[0036] Optionally, the sweep angle of the deformable wing structure can be calculated using the following formula: ; in, Indicates the sweep angle. Represents the arctangent function. This indicates the offset of the leading edge line. Indicates the increase in wingspan.

[0037] Optionally, the dihedral angle of the deformable wing structure can be calculated using the following formula: ; in, Indicates the upper opposite angle. Represents the arctangent function. Indicates the increase in wingspan. This indicates the vertical offset.

[0038] Optionally, the twist angle of the deformable wing structure can be calculated using the following formula: ; in, Indicates the angle of twist. Represents the arctangent function. Represents the wing root chord vector. This represents the reference baseline vector.

[0039] Optionally, the offset of the leading edge line in the chord direction of the corresponding wing of the deformable wing structure can be analyzed by optical measurement techniques, such as digital image correlation (DIC), laser scanning, displacement sensor arrays, etc.

[0040] This invention, through the construction of parameter variation curves along the wingspan, can visually demonstrate the changes of these parameters from the wing root to the wingtip, quickly identify the main characteristics of deformation, and facilitate comparison between the parameter curves of the currently deformed wing and the design state curves. The parameter variation curves refer to the graphical representation of how key geometric parameters (sweep angle, dihedral angle, and twist angle) change with wing span along the wing's span direction.

[0041] Optionally, the parameter variation curve in the wingspan direction can be obtained by determining sampling points in the wingspan direction, extracting key variation parameters corresponding to the sampling points, and fitting the parameter variation curve in the wingspan direction based on the sampling points and the key variation parameters.

[0042] This invention, by combining the parameter variation curves and the parameterized wing cross-section, fits a geometric model of the deformable wing structure that reflects both the actual deformation and the structured geometry. This provides a reliable foundation for subsequent multidisciplinary analysis, including aerodynamics, structure, and control, thereby enabling a more comprehensive understanding and evaluation of the deformable wing's performance and behavior. The wing geometric model refers to a digital representation that includes all the geometric features of the wing.

[0043] As an embodiment of the present invention, the step of fitting the wing geometric model of the deformable wing structure by combining the parameter variation curve and the parameterized wing section includes: Discretize the wingspan direction of the deformable wing structure to obtain the discretized wingspan position; Extract the discretized parameters corresponding to the discretized wingspan position from the parameter variation curve; Based on the discretization parameters, determine the rotation matrix of the discretized wingspan position; Based on the parameterized wing section, calculate the airfoil parameters corresponding to the discretized wingspan position; Based on the airfoil parameters and the rotation matrix, the parameterized wing section corresponding to the discretized wingspan position is fitted with a surface to obtain the initial wing geometric model; The model quality of the initial wing geometry model is detected. When the model quality meets the preset model quality standard, the initial wing geometry model is used as the wing geometry model of the deformable wing structure.

[0044] The discretized wingspan position refers to dividing the continuous coordinate axis along the wingspan direction (from the wing root to the wingtip) into a series of discrete points. The discretization parameters are parameter values ​​extracted from parameter variation curves (such as sweep angle, dihedral angle, and twist angle as a function of wingspan position) and corresponding to the discretized wingspan position. The rotation matrix is ​​a mathematical transformation matrix used to describe the local attitude (such as sweep, dihedral, and twist) of the wing section at the discretized wingspan position. The airfoil parameters are a set of specific values ​​used to define and describe the shape and geometric characteristics of the wing cross-section (i.e., airfoil), such as thickness ratio and camber. The initial wing geometry model refers to the wing model generated for the first time after all calculation and fitting steps have been completed, before quality testing. The model quality refers to a series of standards for evaluating the generated initial wing geometry model, such as geometric accuracy, surface smoothness, and topological correctness. The preset model quality standards refer to a set of specific, quantifiable rules, indicators, and allowable ranges that have been pre-set before model quality testing.

[0045] Optionally, the discretized wingspan position can be obtained using discretization techniques, such as uniform discretization or non-uniform discretization.

[0046] Optionally, the rotation matrix of the discretized wingspan position can be obtained through interpolation and fitting techniques, such as linear interpolation, spline interpolation, quaternion interpolation, etc.

[0047] Optionally, the wing geometry model of the deformable wing structure can be determined by a threshold method. When the model quality does not meet the model quality standard, the fitting parameters of the parameterized wing section corresponding to the discretized wingspan position are adjusted. Based on the fitting parameters, the parameterized wing section corresponding to the discretized wingspan position is fitted to obtain an adjusted wing geometry model. The quality of the adjusted wing geometry model is detected. When the quality of the adjusted model meets the model quality standard, the adjusted wing geometry model is used as the wing geometry model of the deformable wing structure.

[0048] S3. Determine the deformation mode of the deformable wing structure. Based on the deformation mode, calculate the airfoil change and twist angle change of the deformable wing structure during the deformation process. Combine the wing geometry model, the airfoil change, and the twist angle change to fit the initial deformable wing model of the deformable wing structure.

[0049] This invention simplifies the model and reduces computation by determining the deformation mode of the morphing wing structure, thus avoiding overfitting of minor or noisy deformations. The deformation mode refers to the main ways and characteristic forms in which the geometry of the morphing wing structure changes under specific loads, such as bending mode, torsion mode, and thickness change mode.

[0050] Optionally, the deformation mode of the deformable wing structure can be determined by sensor measurement technology, such as strain gauge measurement, displacement sensor, fiber optic grating sensor, etc.

[0051] This invention, by calculating the airfoil change and torsion angle change of the deformable wing structure during deformation according to the deformation mode, can accurately describe the shape change of the wing at each position (along the wingspan, chord, and span) during deformation, thereby calculating the precise geometric shape after deformation. The airfoil change refers to the change in the airfoil geometric parameters at a specific position on the wing relative to its initial state (undeformed state) during deformation. The torsion angle change refers to the change in the rotation angle of the airfoil section about its own quarter chord line relative to the initial state during deformation.

[0052] As an embodiment of the present invention, calculating the airfoil change and twist angle change of the deformable wing structure during the deformation process according to the deformation mode includes: Extract the torsional modal coefficients of the deformation mode; Analyze the torsional deformation function in the deformation mode; Based on the torsional modal coefficients and the torsional deformation function, the change in torsional angle of the deformable wing structure during the deformation process is calculated; Extract the thickness variation coefficient and curvature variation coefficient of the deformation mode; The thickness change of the deformable wing structure is calculated based on the thickness change coefficient. The camber change of the deformable wing structure is calculated based on the camber change coefficient. Based on the thickness change and the camber change, the airfoil change during the deformation process of the deformable wing structure is determined.

[0053] The torsional modal coefficient refers to a weighted parameter describing the degree of torsional deformation of the morphing wing structure during deformation. The torsional deformation function is a mathematical function describing the distribution of the rotation angle of the airfoil section around its longitudinal axis along the wingspan during deformation. The thickness variation coefficient refers to a weighted parameter describing the change in the thickness distribution of the airfoil section during deformation. The camber variation coefficient refers to a weighted parameter describing the change in the camber distribution of the airfoil section during deformation. The thickness variation refers to the change in the thickness parameter of the airfoil section relative to its initial undeformed state during deformation. The camber variation refers to the change in the camber parameter of the airfoil section relative to its initial undeformed state during deformation.

[0054] Optionally, the torsional modal coefficients of the deformation mode can be extracted using finite element analysis methods, such as modal analysis or mesh analysis.

[0055] Optionally, the torsional deformation function in the deformation mode can be determined by measuring the displacement of key points on the wing surface corresponding to the deformable wing structure from different angles using multiple laser displacement sensors, analyzing the displacement change process, extracting the torsional component of the displacement change process, and determining the torsional deformation function in the deformation mode based on the torsional component.

[0056] Optionally, the thickness variation of the deformable wing structure can be calculated using parametric methods, such as the proportional coefficient method or the distribution function method.

[0057] This invention, by combining the wing geometry model, the airfoil change, and the twist angle change, fits an initial deformable wing model of the deformable wing structure. This allows for the precise visualization of the wing's geometric characteristics, providing reliable basic data and model support for subsequent research and design in aerodynamics, structure, control, and other aspects. The initial deformable wing model refers to a model constructed based on the wing's geometry model by introducing and applying geometric parameters describing its shape changes (such as airfoil change and twist angle change), which represents the wing's geometric configuration under specific deformation states.

[0058] As an embodiment of the present invention, the step of fitting an initial deformable wing model of the deformable wing structure by combining the wing geometry model, the airfoil change, and the twist angle change includes: The wing geometry model is meshed to obtain a three-dimensional wing surface mesh, wherein the three-dimensional wing surface mesh includes: ; in, This represents the mesh coordinates of the 3D wing surface mesh when the wing geometry is undeformed. Coordinates representing the wingspan direction, Represents chord coordinates, Represents the coordinates in the wingspan direction Initial distribution of the twist angle at the position, Represents the coordinates in the chord direction Initial thickness distribution at location, Represents the sine function. Represents the cosine function; Determine the initial coordinates of the grid points of the three-dimensional wing surface mesh; Based on the airfoil change and the twist angle change, the initial coordinates of the grid points are updated to obtain the updated airfoil coordinates. Based on the updated airfoil coordinates, the initial deformable wing model of the deformable wing structure is fitted.

[0059] The three-dimensional wing surface mesh refers to a set of small, simple geometric units obtained by discretizing the outer surface of the wing. The initial coordinates of the mesh points refer to the original position coordinates of each mesh vertex in three-dimensional space on the three-dimensional wing surface mesh obtained after meshing the undeformed wing geometric model. The updated airfoil coordinates refer to the new, deformed mesh point coordinates obtained by applying airfoil and twist angle changes to the initial coordinates of the original wing geometric model. The initial twist angle distribution refers to the initial twist angle distribution of each airfoil section (along the wingspan) relative to a reference plane in the undeformed state. The initial thickness distribution refers to the profile shape of the airfoil in the vertical direction (perpendicular to the chord line) in the undeformed state.

[0060] Optionally, the three-dimensional wing surface mesh can be obtained through mesh generation techniques, such as structured meshes, unstructured meshes, and hybrid meshes.

[0061] Optionally, the updated airfoil coordinates can be obtained using the following formula: ; in, This indicates the updated airfoil coordinates. Indicates the grid point in the wingspan direction. The coordinates of each position, Indicates the grid point in the chord direction. The coordinates of each position, Represents the airfoil variation in the chord coordinate system. The component of position change, Represents the coordinates in the wingspan direction The change in the torsional angle of the position. Represents the coordinates in the chord direction Initial thickness distribution at location, Represents the airfoil variation in the chord coordinate system. The amount of thickness change at the location, Represents the sine function. This represents the cosine function.

[0062] S4. Determine the simulation environment of the initial deformable wing model to simulate and calculate the aerodynamic coefficients of the initial deformable wing model, and determine the aerodynamic performance of the initial deformable wing model based on the aerodynamic coefficients.

[0063] This invention, by defining the simulation environment of the initial deformable wing model, creates a highly realistic virtual environment to simulate airflow around the wing, laying the foundation for subsequent analysis of the aerodynamic performance of the initial deformable wing model. The simulation environment refers to a set of calculation conditions, tools, and parameters set up to calculate the aerodynamic coefficients of the initial deformable wing model and analyze its aerodynamic performance.

[0064] Alternatively, the simulation environment for the initial deformable wing model can be determined using computational fluid dynamics.

[0065] This invention quantifies the impact of wing structural deformation on aerodynamic performance by simulating and calculating the aerodynamic coefficients of the initial deformable wing model, providing a data basis for subsequent model adjustments. The aerodynamic coefficients refer to a set of parameters obtained by dimensionlessly converting the aerodynamic forces and moments acting on the initial deformable wing model.

[0066] As an embodiment of the present invention, the simulation calculation of the aerodynamic coefficients of the initial deformable wing model includes: Determine the free flow velocity of the simulation environment corresponding to the initial deformable wing model; Based on the free flow velocity, calculate the dynamic pressure provided by the simulation environment: The lift, drag, and pitching moment of the initial deformable wing model in the simulation environment were detected. Based on the dynamic pressure, lift, drag, and pitching moment, the lift coefficient, drag coefficient, and pitching moment coefficient of the initial deformable wing model are calculated using the following formulas: ; ; ; in, Indicates the lift coefficient. Indicates the drag coefficient. Indicates the pitching moment coefficient. Indicates lift. Indicates dynamic pressure. This represents the projected area of ​​the initial deformable wing model. Indicates resistance. Indicates pitching moment, c represents the wingspan of the initial deformable wing model. Indicates position in the wingspan direction String length, Indicates position Integrate points; The aerodynamic coefficients of the initial deformable wing model are determined based on the lift coefficient, the drag coefficient, and the pitching moment coefficient.

[0067] The free flow velocity refers to the airflow velocity away from the wing surface in a simulation environment or actual flight. The dynamic pressure refers to the kinetic energy of air flowing at velocity V, which exerts pressure on a plane perpendicular to the airflow direction. The lift refers to the force acting on the initial deformable wing model perpendicular to the airflow direction. The drag refers to the force acting on the initial deformable wing model, along the airflow direction, that hinders the object's motion. The pitching moment refers to the moment acting on the initial deformable wing model, causing it to rotate about a transverse axis (perpendicular to the wingspan and flight direction) passing through its leading edge. The lift coefficient is a dimensionless parameter measuring the object's ability to generate lift. The drag coefficient is a dimensionless parameter measuring the magnitude of drag experienced by the object. The pitching moment coefficient is a dimensionless parameter measuring the object's ability to generate a pitching moment about a reference point. The projected area refers to the wing's projected area perpendicular to the incoming flow direction.

[0068] Optionally, the dynamic pressure provided by the simulation environment can be calculated using the following formula: ; in, Indicates dynamic pressure. This represents the air density of the simulated environment. Indicates free velocity.

[0069] Optionally, the free flow velocity of the simulation environment corresponding to the initial deformable wing model can be determined by averaging the velocity at the inlet boundary.

[0070] Optionally, the lift, drag, and pitching moment of the initial deformable wing model in the simulation environment can be determined by computational fluid dynamics. The wing surface pressure and shear stress of the initial deformable wing model can be determined by integrating the wing surface pressure and the shear stress in different directions to obtain the lift, drag, and pitching moment.

[0071] This invention, through the determination of the aerodynamic performance of the initial deformable wing model based on the aerodynamic coefficients, can be used to evaluate the effects of specific deformation modes (such as changes in camber and twist angle) on increasing lift, reducing drag, improving stability, and enhancing maneuverability. The aerodynamic performance refers to the aerodynamic forces acting on the initial deformable wing model as it moves through the air, and the various flight characteristics exhibited as a result.

[0072] As an embodiment of the present invention, determining the aerodynamic performance of the initial deformable wing model based on the aerodynamic coefficients includes: Indeed, the test elevation angle of the initial deformable wing model was determined; Construct the coefficient-angle curves for the aerodynamic coefficients and the test elevation angle; Identify the stall angle of attack, drag variation state, and pitching moment characteristics of the coefficient-angle curve; The aerodynamic performance of the initial deformable wing model is determined based on the stall angle of attack, the drag variation state, and the pitching moment characteristics.

[0073] The test angle of attack refers to the angle between the chord line of the initial deformable wing model and the relative airflow direction (or free velocity direction). The coefficient-angle curve is a curve plotted based on the variation of aerodynamic coefficients (such as lift coefficient, drag coefficient, and pitching moment coefficient) with the test angle of attack. The stall angle of attack is the angle of attack corresponding to the point where the lift coefficient reaches its maximum value and begins to decrease sharply. The induced drag change state refers to the pattern and characteristics of the drag coefficient change during the test angle of attack. The pitching moment characteristic refers to the magnitude and variation of the rotational tendency of the initial deformable wing model around its transverse axis as the test angle of attack changes under the influence of airflow.

[0074] Optionally, the coefficient-angle curves of the aerodynamic coefficients and the test elevation angle can be constructed using methods such as linear regression, polynomial fitting, or linearized nonlinear fitting.

[0075] Optionally, the stall angle of attack of the coefficient-angle curve can be determined by identifying the inflection point of sharp drop in lift in the lift coefficient-angle curve and extracting the angle value of the inflection point of sharp drop in lift.

[0076] Optionally, the resistance change state of the coefficient-angle curve can be determined by identifying the change in the slope of the resistance coefficient-angle curve within the coefficient-angle curve.

[0077] Optionally, the pitch moment characteristics of the coefficient-angle curve can be identified using numerical differentiation.

[0078] S5. Based on the aerodynamic performance, optimize the initial deformable wing model to obtain the target deformable wing model.

[0079] This invention optimizes the initial deformable wing model based on its aerodynamic performance, resulting in a target deformable wing model that improves multiple key aerodynamic characteristics such as lift, drag, stability, and maneuverability, ultimately yielding a high-quality deformable wing model. The target deformable wing model refers to a wing geometry model that, after optimization, achieves specific aerodynamic performance targets and deformation patterns.

[0080] As an embodiment of the present invention, the step of optimizing the initial deformable wing model based on the aerodynamic performance to obtain the target deformable wing model includes: Determine whether the aerodynamic performance meets the preset aerodynamic performance standard; When the aerodynamic performance does not meet the aerodynamic performance standard, identify the influence parameters of the initial deformable wing model; Based on the influencing parameters, the initial deformable wing model is optimized to obtain the optimized deformable wing model; Calculate the optimized aerodynamic coefficients of the optimized deformable wing model to analyze its optimized aerodynamic performance; When the optimized aerodynamic performance meets the aerodynamic performance standard, the optimized deformable wing model is used as the target deformable wing model.

[0081] The preset aerodynamic performance standards refer to a series of specific technical indicators set in advance during aerodynamic optimization. The influencing parameters refer to geometric parameters that significantly affect the aerodynamic performance of the deformable wing model, such as wing area, thickness distribution, and deformation amplitude. The optimized deformable wing model refers to the deformable wing model that meets the predetermined aerodynamic performance standards after a series of optimization design and analysis processes. The optimized aerodynamic coefficients refer to the aerodynamic performance parameters calculated for the newly obtained optimized deformable wing model after completing the optimization design of the initial deformable wing model. The optimized aerodynamic performance refers to the aerodynamic characteristics exhibited by the optimized deformable wing model.

[0082] Optionally, the optimized deformable wing model can be updated using a multi-objective optimization algorithm, such as the NSGA-II algorithm or the SPEA2 algorithm.

[0083] Compared to the problems described in the background art, the embodiments of the present invention, by fitting the upper and lower surface curves of the deformable wing structure based on the key points of the wing section, can transform the geometric data of the deformable wing from a discrete set of points into a computable and optimizable continuous model, laying the foundation for subsequent simulation, control, and manufacturing. Optionally, by combining the upper and lower surface curves, the embodiments of the present invention determine that the parameterized wing section of the deformable wing structure can accurately reconstruct the geometry of the original wing section through precise fitting of the upper and lower surface curves. Furthermore, by combining the parameter variation curves and the parameterized wing section, the embodiments of the present invention can fit a wing geometric model of the deformable wing structure that reflects both real deformation and structure, providing a reliable foundation for subsequent multidisciplinary analysis in aerodynamics, structure, and control, thereby enabling a more comprehensive understanding and evaluation of deformable wings. The invention provides a method and system for rapid modeling and simulation of deformable wing structures. By combining the wing geometry model, airfoil variation, and torsion angle variation, the initial deformable wing model of the deformable wing structure can be fitted to accurately and visually represent the geometric characteristics of the deformable wing, providing reliable basic data and model support for subsequent aerodynamic, structural, and control research and design. Furthermore, by determining the aerodynamic performance of the initial deformable wing model based on the aerodynamic coefficients, the invention can evaluate the effects of specific deformation modes (such as changing camber and torsion angle) on improving lift, reducing drag, and enhancing stability and maneuverability. Finally, by optimizing the initial deformable wing model based on the aerodynamic performance, the invention obtains a target deformable wing model that improves multiple key aerodynamic characteristics such as lift, drag, stability, and maneuverability, ultimately resulting in a high-quality deformable wing model. Therefore, the rapid modeling and simulation method and system for deformable wing structures provided by this invention can improve the accuracy and design efficiency of deformable wing structure modeling and simulation.

[0084] Example 2: like Figure 2 The diagram shown is a functional block diagram of a rapid modeling and simulation system for deformable wing structures according to the present invention.

[0085] The rapid modeling and simulation system 200 for deformable wing structures described in this invention can be installed in an electronic device. Depending on the functions implemented, the rapid modeling and simulation system for deformable wing structures may include a parametric wing section module 201, a wing geometry model construction module 202, a deformable wing model construction module 203, an aerodynamic performance analysis module 204, and a target deformable wing model module 205. The modules described in this invention can also be referred to as units, which are a series of computer program segments that can be executed by the processor of an electronic device and perform a fixed function, and are stored in the memory of the electronic device.

[0086] In this embodiment of the invention, the functions of each module / unit are as follows: The parameterized wing section module 201 is used to collect wing section data of the deformable wing structure and identify key points of the wing section data. The key points of the wing section include: leading edge point, trailing edge point and maximum thickness point. Based on the key points of the wing section, the upper surface curve and lower surface curve of the deformable wing structure are fitted. Combining the upper surface curve and the lower surface curve, the parameterized wing section of the deformable wing structure is determined. The wing geometry model construction module 202 is used to analyze the key variation parameters of the deformable wing structure in the wingspan direction, wherein the key variation parameters include: sweep angle, dihedral angle and twist angle, so as to construct the parameter variation curve in the wingspan direction, and combine the parameter variation curve and the parameterized wing section to fit the wing geometry model of the deformable wing structure. The deformable wing model construction module 203 is used to determine the deformation mode of the deformable wing structure, calculate the airfoil change and twist angle change of the deformable wing structure during the deformation process based on the deformation mode, and fit the initial deformable wing model of the deformable wing structure by combining the wing geometric model, the airfoil change and the twist angle change. The aerodynamic performance analysis module 204 is used to determine the simulation environment of the initial deformable wing model, to simulate and calculate the aerodynamic coefficients of the initial deformable wing model, and to determine the aerodynamic performance of the initial deformable wing model based on the aerodynamic coefficients. The target deformable wing model module 205 is used to optimize the initial deformable wing model based on the aerodynamic performance to obtain the target deformable wing model.

[0087] In detail, the modules in the rapid modeling and simulation system 200 for deformable wing structures described in this embodiment of the invention employ the same methods as described above. Figure 1 The method uses the same techniques as the rapid modeling and simulation method for deformable wing structures described in the previous section, and can produce the same technical effects, so it will not be elaborated here.

[0088] It will be apparent to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above, and that the present invention can be implemented in other specific forms without departing from the spirit or essential characteristics of the present invention.

[0089] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and are not intended to limit it. Although the present invention has been described in detail with reference to preferred embodiments, those skilled in the art should understand that modifications or equivalent substitutions can be made to the technical solutions of the present invention without departing from the spirit and scope of the technical solutions of the present invention.

Claims

1. A morphing wing structure rapid modeling simulation method, characterized in that, The method comprises: Collecting wing section data of a morphing wing structure, identifying wing section key points of the wing section data, wherein the wing section key points comprise a leading edge point, a trailing edge point and a maximum thickness point, fitting upper surface curves and lower surface curves of the morphing wing structure according to the wing section key points, determining parameterized wing sections of the morphing wing structure in combination with the upper surface curves and the lower surface curves; Analyzing key change parameters of the morphing wing structure corresponding to a wingspan direction, wherein the key change parameters comprise a sweepback angle, a dihedral angle and a twist angle, constructing a parameter change curve of the wingspan direction, fitting a wing geometry model of the morphing wing structure in combination with the parameter change curve and the parameterized wing sections; Determining a morphing mode of the morphing wing structure, calculating a wing profile change amount and a twist angle change amount of the morphing wing structure in a morphing process according to the morphing mode, fitting an initial morphing wing model of the morphing wing structure in combination with the wing geometry model, the wing profile change amount and the twist angle change amount; Determining a simulation environment of the initial morphing wing model to simulate and calculate aerodynamic force coefficients of the initial morphing wing model, determining aerodynamic performance of the initial morphing wing model according to the aerodynamic force coefficients; Optimizing the initial morphing wing model according to the aerodynamic performance to obtain a target morphing wing model.

2. The morphing wing structure rapid modeling and simulation method of claim 1, wherein, The fitting of the upper surface curves and the lower surface curves of the morphing wing structure according to the wing section key points comprises: Calculating a chord length and a maximum thickness value of the morphing wing structure according to the wing section key points; Dividing the morphing wing structure into a leading edge interval, a middle interval and a trailing edge interval; Polynomial fitting is respectively performed on the leading edge interval, the middle interval and the trailing edge interval to obtain leading edge upper and lower surface curves, middle upper and lower surface curves and trailing edge upper and lower surface curves; Defining a constraint condition at an interface between the leading edge interval, the middle interval and the trailing edge interval; According to the constraint condition at the interface, curve splicing is respectively performed on the leading edge upper and lower surface curves, the middle upper and lower surface curves and the trailing edge upper and lower surface curves to obtain spliced upper surface curves and spliced lower surface curves; Determining upper surface curve error terms and lower surface curve error terms of the spliced upper surface curves and the spliced lower surface curves; According to the upper surface curve error terms and the lower surface curve error terms, smoothing the spliced upper surface curves and the spliced lower surface curves to obtain upper surface curves and lower surface curves.

3. The morphing wing structure rapid modeling and simulation method of claim 1, wherein, The analysis of the key change parameters of the morphing wing structure corresponding to the wingspan direction comprises: Identifying a leading edge line of the morphing wing structure, analyzing a leading edge line offset of the leading edge line in a wing chord direction of the morphing wing structure; Determining a wingspan increment of the wingspan direction, calculating a sweepback angle of the morphing wing structure according to the wingspan increment and the leading edge line offset; measuring a vertical offset of a leading edge point of the morphing wing structure, calculating an upwash angle of the morphing wing structure according to the vertical offset and the wing span increment; defining a reference baseline of the morphing wing structure, calculating a reference baseline vector of the reference baseline; determining a wing root chord line vector of the morphing wing structure, calculating a twist angle of the morphing wing structure according to the wing root chord line vector and the reference baseline vector; determining a key variation parameter of the morphing wing structure in a wing span direction according to the back-sweep angle, the upwash angle and the twist angle.

4. The morphing wing structure rapid modeling and simulation method of claim 1, wherein, the fitting of the wing geometry model of the morphing wing structure in combination with the parameter variation curve and the parameterized wing section includes: discretizing the morphing wing structure in the wing span direction to obtain discrete wing span positions; extracting discrete parameters corresponding to the discrete wing span positions from the parameter variation curve; determining a rotation matrix of the discrete wing span positions according to the discrete parameters; calculating airfoil parameters corresponding to the discrete wing span positions according to the parameterized wing section; performing surface fitting on the parameterized wing section corresponding to the discrete wing span positions according to the airfoil parameters and the rotation matrix to obtain an initial wing geometry model; detecting a model quality of the initial wing geometry model, and taking the initial wing geometry model as the wing geometry model of the morphing wing structure when the model quality meets a preset model quality standard.

5. The morphing wing structure rapid modeling and simulation method of claim 1, wherein, the calculation of the airfoil variation and the twist angle variation of the morphing wing structure in the morphing process according to the morphing mode includes: extracting twist modal coefficients of the morphing mode; analyzing a twist deformation function in the morphing mode; calculating the twist angle variation of the morphing wing structure in the morphing process according to the twist modal coefficients and the twist deformation function; extracting thickness variation coefficients and camber variation coefficients of the morphing mode; calculating a thickness variation of the morphing wing structure according to the thickness variation coefficients; calculating a camber variation of the morphing wing structure according to the camber variation coefficients; determining an airfoil variation of the morphing wing structure in the morphing process based on the thickness variation and the camber variation.

6. The morphing wing structure rapid modeling and simulation method of claim 1, wherein, the fitting of the initial morphing wing model of the morphing wing structure in combination with the wing geometry model, the airfoil variation and the twist angle variation includes: meshing the wing geometry model to obtain a three-dimensional wing surface mesh, wherein the three-dimensional wing surface mesh includes: ； wherein represents the grid coordinates of the three-dimensional wing surface mesh when the wing geometry model is not deformed, represents the coordinate in the spanwise direction, represents the coordinate in the chordwise direction, represents the initial distribution of twist angle at the position of the spanwise coordinate , represents the initial distribution of thickness at the position of the chordwise coordinate , represents the sine function, represents the cosine function; determining initial coordinates of mesh points of the three-dimensional wing surface mesh; updating the initial coordinates of the mesh points to obtain updated airfoil coordinates according to the airfoil variation and the twist angle variation; fitting the initial morphing wing model of the morphing wing structure according to the updated airfoil coordinates.

7. The morphing wing structure rapid modeling and simulation method of claim 1, wherein, the simulation of the aerodynamic force coefficients of the initial morphing wing model includes: determining a free flow velocity of a simulation environment corresponding to the initial morphing wing model; calculating a dynamic pressure provided by the simulation environment according to the free flow velocity; detecting lift, drag and pitching moment of the initial morphing wing model in the simulation environment; calculating lift coefficient, drag coefficient and pitching moment coefficient of the initial morphing wing model according to the dynamic pressure, the lift, the drag and the pitching moment by using the following formula: ； ； ； wherein, denotes the lift coefficient, denotes the drag coefficient, denotes the pitching moment coefficient, denotes the lift, denotes the dynamic pressure, denotes the projected area of the initial morphing wing model, denotes the drag, denotes the pitching moment, denotes the span length of the initial morphing wing model, c denotes the chord length at a position in the span direction, denotes the integration over the position ; determining aerodynamic force coefficients of the initial morphing wing model according to the lift coefficient, the drag coefficient and the pitching moment coefficient.

8. The morphing wing structure rapid modeling and simulation method of claim 1, wherein, determining aerodynamic performance of the initial morphing wing model according to the aerodynamic force coefficients, including: detecting test angles of attack of the initial morphing wing model; constructing coefficient-angle curves of the aerodynamic force coefficients and the test angles of attack; identifying stall angles of attack, drag change states and pitching moment characteristics of the coefficient-angle curves; determining aerodynamic performance of the initial morphing wing model according to the stall angles of attack, the drag change states and the pitching moment characteristics.

9. The morphing wing structure rapid modeling and simulation method of claim 1, wherein, optimizing the initial morphing wing model according to the aerodynamic performance to obtain a target morphing wing model, including: judging whether the aerodynamic performance meets preset aerodynamic performance standards; when the aerodynamic performance does not meet the aerodynamic performance standards, identifying influence parameters of the initial morphing wing model; optimizing the initial morphing wing model according to the influence parameters to obtain an optimized morphing wing model; calculating optimized aerodynamic coefficients of the optimized morphing wing model to analyze optimized aerodynamic performance of the optimized morphing wing model; when the optimized aerodynamic performance meets the aerodynamic performance standards, taking the optimized morphing wing model as the target morphing wing model.

10. A morphing wing structure rapid modeling simulation system, characterized in that, The system includes: a parameterized wing section module configured to collect wing section data of a morphing wing structure, identify wing section key points of the wing section data, wherein the wing section key points include a leading edge point, a trailing edge point and a maximum thickness point, fit upper surface curves and lower surface curves of the morphing wing structure according to the wing section key points, and determine a parameterized wing section of the morphing wing structure in combination with the upper surface curves and the lower surface curves; a wing geometry model construction module configured to analyze key change parameters of the morphing wing structure in a corresponding wing span direction, wherein the key change parameters include a sweep angle, a dihedral angle and a twist angle, construct a parameter change curve of the wing span direction, and fit a wing geometry model of the morphing wing structure in combination with the parameter change curve and the parameterized wing section; a morphing wing model construction module configured to determine a morphing mode of the morphing wing structure, calculate wing profile change amounts and twist angle change amounts of the morphing wing structure in a morphing process according to the morphing mode, and fit an initial morphing wing model of the morphing wing structure in combination with the wing geometry model, the wing profile change amounts and the twist angle change amounts; an aerodynamic performance analysis module configured to determine a simulation environment of the initial morphing wing model, simulate and calculate aerodynamic force coefficients of the initial morphing wing model, and determine aerodynamic performance of the initial morphing wing model according to the aerodynamic force coefficients. a target morphing wing model module, configured to optimize the initial morphing wing model according to the aerodynamic performance to obtain a target morphing wing model.

Images