CN-121765849-B - Quick modeling simulation method and system for deformed wing structure

CN121765849BCN 121765849 BCN121765849 BCN 121765849BCN-121765849-B

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, wherein the rapid modeling simulation method comprises the steps of identifying 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; the method comprises the steps of analyzing key variation parameters of a deformed wing structure corresponding to a wingspan direction to construct a parameter variation curve in the wingspan direction, fitting a wing geometric model of the deformed wing structure, determining a deformation mode of the deformed wing structure, calculating wing profile variation and torsion angle variation of the deformed wing structure in a deformation process, fitting an initial deformed wing model of the deformed wing structure, simulating and calculating aerodynamic coefficients of the initial deformed wing model, determining aerodynamic performance of the initial deformed wing model, and optimizing the initial deformed wing model to obtain a target deformed wing model. The invention can improve the accuracy and design efficiency of modeling simulation of the deformed wing structure.

Inventors

JIA ZHAOHU
CHENG LONGFEI
Min rong
MA CHUNHAO
WANG ANWEN
HU KEJUN

Assignees

西北工业大学

Dates

Publication Date: 20260505
Application Date: 20260305

Claims (10)

1. A method for rapid modeling simulation of a deformed wing structure, the method comprising: Acquiring wing section data of a deformed wing structure, and identifying wing section key points of the wing section data, wherein the wing section key points comprise a front edge point, a rear edge point and a maximum thickness point, and fitting an upper surface curve and a lower surface curve of the deformed wing structure according to the wing section key points, and determining a parameterized wing section of the deformed wing structure by combining the upper surface curve and the lower surface curve; analyzing key variation parameters of the deformed wing structure corresponding to the wingspan direction, wherein the key variation parameters comprise a sweepback angle, a dihedral angle and a torsion angle, so as to construct a parameter variation curve of the wingspan direction, and fitting a wing geometric model of the deformed wing structure by combining the parameter variation curve and the parameterized wing section; Determining a deformation mode of the deformed wing structure, calculating wing profile variation and torsion angle variation of the deformed wing structure in the deformation process according to the deformation mode, and fitting an initial deformed wing model of the deformed wing structure by combining the wing geometric model, the wing profile variation and the torsion angle variation; Determining a simulation environment of the initial deformed wing model to simulate and calculate aerodynamic coefficients of the initial deformed wing model, and determining aerodynamic performance of the initial deformed wing model according to the aerodynamic coefficients; And optimizing the initial deformed wing model according to the aerodynamic performance to obtain a target deformed wing model.
2. The method for rapid modeling simulation of a deformed wing structure according to claim 1, wherein the fitting the upper surface curve and the lower surface curve of the deformed wing structure according to the wing section key points comprises: calculating the chord length and the maximum thickness value of the deformed wing structure according to the wing section key points; dividing the deformed wing structure into a front edge section, a middle section and a rear edge section; Respectively performing polynomial fitting on the front edge interval, the middle section interval and the rear edge interval to obtain a front edge upper and lower surface curve, a middle section upper and lower surface curve and a rear edge upper and lower surface curve; Defining boundary constraint conditions among the front edge interval, the middle section interval and the rear edge interval; According to the constraint conditions of the junction, respectively performing curve splicing on the upper and lower surface curves of the front edge, the upper and lower surface curves of the middle section and the upper and lower surface curves of the rear edge to obtain a spliced upper surface curve and a spliced lower surface curve; Determining an upper surface curve error term and a lower surface curve error term of the spliced upper surface curve and the spliced lower surface curve; And smoothing the spliced upper surface curve and the spliced lower surface curve according to the upper surface curve error item and the lower surface curve error item to obtain an upper surface curve and a lower surface curve.
3. The method for rapid modeling simulation of a deformed wing structure according to claim 1, wherein the analyzing key variation parameters of the deformed wing structure corresponding to a spanwise direction comprises: identifying a front edge line of the deformed wing structure, and analyzing the front edge line offset of the front edge line in the chord-wise direction of the corresponding machine wing of the deformed wing structure; Determining the wingspan increment in the wingspan direction, and calculating the sweepback angle of the deformed wing structure according to the wingspan increment and the front edge line offset; Measuring the vertical offset of the corresponding front edge point of the deformed wing structure, and calculating the dihedral angle of the deformed wing structure according to the vertical offset and the span increment; defining a reference baseline of the deformed wing structure, and calculating a reference baseline vector of the reference baseline; determining a root chord line vector of the deformed wing structure, and calculating a torsion angle of the deformed wing structure according to the root chord line vector and the reference baseline vector; And determining key variation parameters of the deformed wing structure corresponding to the wingspan direction according to the sweepback angle, the dihedral angle and the torsion angle.
4. The method for rapid modeling simulation of a deformed wing structure according to claim 1, wherein the fitting the wing geometric model of the deformed wing structure by combining the parameter variation curve and the parameterized wing section comprises: discretizing the corresponding wingspan direction of the deformed wing structure to obtain a discretized wingspan position; extracting discretization parameters corresponding to the discretization span positions from the parameter change curve; Determining a rotation matrix of the discretized span position according to the discretized parameters; calculating airfoil parameters corresponding to the discretized wingspan positions according to the parameterized airfoil sections; performing surface fitting on the parameterized wing section corresponding to the discretized wing span position according to the wing section parameters and the rotation matrix to obtain an initial wing geometric model; Detecting the model quality of the initial wing geometric model, and taking the initial wing geometric model as the wing geometric model of the deformed wing structure when the model quality meets a preset model quality standard.
5. The rapid modeling simulation method of a deformed wing structure according to claim 1, wherein calculating an airfoil variation and a torsion angle variation of the deformed wing structure during deformation according to the deformation mode comprises: Extracting a torsional mode coefficient of the deformation mode; analyzing a torsional deformation function in the deformation mode; calculating the torsion angle variation of the deformed wing structure in the deformation process according to the torsion mode coefficient and the torsion deformation function; extracting a thickness change coefficient and a camber change coefficient of the deformation mode; calculating the thickness variation of the deformed wing structure according to the thickness variation coefficient; Calculating the bending variation of the deformed wing structure according to the bending variation coefficient; And determining the airfoil profile variation of the deformed wing structure in the deformation process based on the thickness variation and the camber variation.
6. The method of rapid modeling simulation of a deformed wing structure according to claim 1, wherein said fitting an initial deformed wing model of the deformed wing structure in combination with the wing geometry model, the airfoil variation and the torsion angle variation comprises: Gridding the wing geometric model to obtain a three-dimensional wing surface grid, wherein the three-dimensional wing surface grid comprises: ; Wherein, the Representing grid coordinates of a three-dimensional wing surface grid when the wing geometric model is not deformed, The coordinates in the spanwise direction are indicated, The chordwise coordinates are represented as such, Expressed in spanwise coordinates The torsion angle of the position is initially distributed, Expressed in chordwise coordinates The thickness of the locations is initially distributed, The representation of a sinusoidal function is given, Representing a cosine function; determining initial coordinates of grid points of the three-dimensional wing surface grid; updating the initial coordinates of the grid points according to the airfoil change amount and the torsion angle change amount to obtain updated airfoil coordinates; and fitting an initial deformed wing model of the deformed wing structure according to the updated wing profile coordinates.
7. The method for rapid modeling simulation of a morphing wing structure according to claim 1, wherein the simulating calculation of aerodynamic coefficients of the initial morphing wing model comprises: Determining the free flow rate of the simulation environment corresponding to the initial deformed wing model; calculating dynamic pressure provided by the simulation environment according to the free flow rate; detecting the lift force, the resistance and the pitching moment of the initial deformation wing model in the simulation environment; According to the dynamic pressure, the lifting force, the resistance and the pitching moment, the lifting force coefficient, the resistance coefficient and the pitching moment coefficient of the initial deformation wing model are calculated by the following formulas: ; ; ; Wherein, the Representing the coefficient of lift, Represents the coefficient of resistance and, Representing the pitch moment coefficient of the wind turbine, Which represents the lift force and, The dynamic pressure is indicated by the expression, Representing the projected area of the initially deformed wing model, The resistance is indicated by the expression of the resistance, Representing the moment of pitch and the moment of pitch, Representing the span length of an initially deformed wing model, c Indicating spanwise position Is used for the length of the chord of the (c), Indicating the position of the pair Integrating; and determining the aerodynamic coefficient of the initial deformed wing model according to the lift coefficient, the resistance coefficient and the pitching moment coefficient.
8. The method for rapid modeling simulation of a deformed wing structure according to claim 1, wherein determining aerodynamic performance of the initial deformed wing model according to the aerodynamic coefficient comprises: The test elevation angle of the initial deformation wing model is truly measured; Constructing a coefficient-angle curve of the aerodynamic coefficient and the test elevation angle; identifying stall angle of attack, resistance change state and pitching moment characteristics of the coefficient-angle curve; and determining the aerodynamic performance of the initial deformation wing model according to the stall attack angle, the resistance change state and the pitching moment characteristic.
9. The method for rapid modeling simulation of a deformed wing structure according to claim 1, wherein optimizing the initial deformed wing model according to the aerodynamic performance to obtain a target deformed wing model comprises: Judging whether the pneumatic performance meets a preset pneumatic performance standard or not; identifying influencing parameters of the initial deformed wing model when the aerodynamic performance does not meet the aerodynamic performance criteria; Optimizing the initial deformed wing model according to the influence parameters to obtain an optimized deformed wing model; calculating an optimized aerodynamic coefficient of the optimized deformed wing model to analyze the optimized aerodynamic performance of the optimized deformed wing model; and when the optimized aerodynamic performance meets the aerodynamic performance standard, taking the optimized deformed wing model as a target deformed wing model.
10. A morphing wing structure rapid modeling simulation system, the system comprising: The parameterized wing section module is used for acquiring wing section data of the deformed wing structure and identifying wing section key points of the wing section data, wherein the wing section key points comprise a front edge point, a rear edge point and a maximum thickness point, and according to the wing section key points, an upper surface curve and a lower surface curve of the deformed wing structure are fitted, and the parameterized wing section of the deformed wing structure is determined by combining the upper surface curve and the lower surface curve; The wing geometric model construction module is used for analyzing key variation parameters of the deformed wing structure corresponding to the wingspan direction, wherein the key variation parameters comprise a sweepback angle, an dihedral angle and a torsion angle so as to construct a parameter variation curve of the wingspan direction, and fitting a wing geometric model of the deformed wing structure by combining the parameter variation curve and the parameterized wing section; The deformation wing model construction module is used for determining a deformation mode of the deformation wing structure, calculating wing profile variation and torsion angle variation of the deformation wing structure in the deformation process according to the deformation mode, and fitting an initial deformation wing model of the deformation wing structure by combining the wing geometric model, the wing profile variation and the torsion angle variation; the aerodynamic performance analysis module is used for determining the simulation environment of the initial deformed wing model so as to simulate and calculate the aerodynamic coefficient of the initial deformed wing model, and determining the aerodynamic performance of the initial deformed wing model according to the aerodynamic coefficient; And the target deformation wing model module is used for optimizing the initial deformation wing model according to the aerodynamic performance to obtain a target deformation wing model.

Description

Quick modeling simulation method and system for deformed wing structure Technical Field The invention relates to a rapid modeling simulation method and system for a deformed wing structure, and belongs to the technical field of computer simulation. Background The rapid modeling simulation of the deformed wing structure refers to a method which is specially used for the wing structure capable of changing the shape of the wing structure (for example, by changing the wing shape, the torsion angle, the spanwise shape and the like) and can complete the geometric modeling, the physical model establishment and the subsequent performance (mainly pneumatic and structural mechanical performance) simulation of the deformed wing structure in a short time. The rapid modeling simulation of the deformed wing structure can efficiently evaluate the influence of different deformation strategies on performances of the aircraft in various aspects such as aerodynamic efficiency, structural efficiency, operability and stability, and the like, thereby helping to design the aircraft which can really utilize deformation advantages and realize performance spanning. The traditional deformed wing structural modeling builds a geometric model through complex NURBS, B spline and other methods, and the method needs to define a large number of control points, weights, node vectors and the like because of building a complete wing geometric model, and each detail needs to be carefully adjusted, so that the process is complicated, the precise control is difficult, and the precise and rapid control of complex geometric shapes and deformation modes is difficult. Disclosure of Invention The invention provides a rapid modeling simulation method and system for a deformed wing structure, and mainly aims to improve the accuracy and design efficiency of modeling simulation of the deformed wing structure. In order to achieve the above purpose, the invention provides a rapid modeling simulation method for a deformed wing structure, which comprises the following steps: Acquiring wing section data of a deformed wing structure, and identifying wing section key points of the wing section data, wherein the wing section key points comprise a front edge point, a rear edge point and a maximum thickness point, and fitting an upper surface curve and a lower surface curve of the deformed wing structure according to the wing section key points, and determining a parameterized wing section of the deformed wing structure by combining the upper surface curve and the lower surface curve; analyzing key variation parameters of the deformed wing structure corresponding to the wingspan direction, wherein the key variation parameters comprise a sweepback angle, a dihedral angle and a torsion angle, so as to construct a parameter variation curve of the wingspan direction, and fitting a wing geometric model of the deformed wing structure by combining the parameter variation curve and the parameterized wing section; Determining a deformation mode of the deformed wing structure, calculating wing profile variation and torsion angle variation of the deformed wing structure in the deformation process according to the deformation mode, and fitting an initial deformed wing model of the deformed wing structure by combining the wing geometric model, the wing profile variation and the torsion angle variation; Determining a simulation environment of the initial deformed wing model to simulate and calculate aerodynamic coefficients of the initial deformed wing model, and determining aerodynamic performance of the initial deformed wing model according to the aerodynamic coefficients; And optimizing the initial deformed wing model according to the aerodynamic performance to obtain a target deformed wing model. Optionally, the fitting the upper surface curve and the lower surface curve of the deformed wing structure according to the wing section key points includes: calculating the chord length and the maximum thickness value of the deformed wing structure according to the wing section key points; dividing the deformed wing structure into a front edge section, a middle section and a rear edge section; Respectively performing polynomial fitting on the front edge interval, the middle section interval and the rear edge interval to obtain a front edge upper and lower surface curve, a middle section upper and lower surface curve and a rear edge upper and lower surface curve; Defining boundary constraint conditions among the front edge interval, the middle section interval and the rear edge interval; According to the constraint conditions of the junction, respectively performing curve splicing on the upper and lower surface curves of the front edge, the upper and lower surface curves of the middle section and the upper and lower surface curves of the rear edge to obtain a spliced upper surface curve and a spliced lower surface curve; Determining an upper surface curve error term and a lower surf