Fabric preform initial shape optimization cutting method based on finite element simulation

Abstract

The invention belongs to the field of composite material manufacturing process simulation and optimization design, and particularly relates to a fabric preform initial shape optimization cutting method based on finite element simulation, which comprises the following steps: loading a parameterized simulation and evaluation model for fabric shape regulation and control, and outputting a maximum value of a fiber main direction compression strain absolute value; polar coordinates of control points in the simulation and evaluation model are initialized, and the value range of the polar coordinates is determined; and then an optimization target and constraint conditions of the simulation and evaluation model are set in Isight software based on a design target, and an optimization algorithm is selected for operation calculation until an optimal solution is obtained. The fabric shape optimal solution corresponding to the minimum fabric forming defect characterization quantity can be obtained through numerical simulation calculation, repeated trial and error based on a large number of fabric forming physical tests are avoided, and the process design time and cost can be effectively saved; the fabric shape is used as an optimization design variable, and the material consumption can be saved by setting the maximum area constraint of the fabric.

Description

Technical Field

[0001] This application belongs to the field of composite material manufacturing process simulation and optimization design, and particularly relates to an optimized cutting method for the initial shape of a fabric preform based on finite element simulation. Background Art

[0002] The liquid molding technology based on the infiltration of dry fiber preforms by liquid resin is an important way to rapidly and low-costly prepare composite materials. As an important link in the composite material liquid molding process, two-dimensional dry fiber fabrics need to be extruded and shaped by a mold to obtain a flexible preform adapted to the three-dimensional geometric shape of the component, and then infiltrated and cured by liquid resin to obtain the final composite material component. Therefore, the fiber orientation uniformity in the preform is crucial for the mechanical properties of the composite material product. However, during the forming process of dry fiber fabrics, there are problems such as large fabric deformation, difficult control of boundary constraints, and mutual extrusion and friction between the mold and the fabric, which are likely to induce manufacturing defects such as fabric wrinkles, fiber buckling, and fiber breakage, thereby reducing the mechanical properties and quality consistency of the composite material product. It can be seen that how to suppress the occurrence of manufacturing defects during the fabric forming stage is an important difficulty in ensuring the performance of composite materials.

[0003] Regarding the suppression of forming defects in composite material preforms, relevant researchers have carried out a large amount of work.

[0004] The literature "Inter-ply stitching optimisation of highly drapeable multi-ply preforms" first proposed the preform defect quantification evaluation index based on the axial compression strain of fabric fibers adopted in this patent, and optimized the design of the interlayer suture positions of multi-layer fabrics; the literature "Formability optimisation of fabric preforms by controlling material draw-in through in-plane constraints" proposed an optimization method for the clamping position and clamping stiffness of the fabric boundary with the goal of minimizing the fabric shear strain; the literature "Optimisation of intra-ply stitch removal for improved formability of biaxial non-crimp fabrics" proposed an optimized design method for the selective removal of intra-layer sutures of non-crimp fabrics with the goal of minimizing the fabric shear strain and the intra-layer suture area of the fabric, achieving the occurrence of fold defects in the preform. However, the design variables adopted in the above three optimization design methods in the literature are different from the fabric boundary shapes adopted in this patent.

[0005] Therefore, how to more effectively suppress manufacturing defects is a problem that needs to be solved. Summary of the Invention

[0006] The purpose of this application is to provide an initial shape optimization cutting method for fabric preforms based on finite element simulation to solve the problem of difficult to effectively suppress manufacturing defects in the prior art.

[0007] The technical solution of this application is: an initial shape optimization cutting method for fabric preforms based on finite element simulation, including:

[0008] Obtain the initial configuration data of the two-dimensional fiber fabric and input it into the Abaqus platform; obtain the unit direction vector in the initial configuration data, then construct an orthogonal coordinate system using the unit direction vector, and calculate the transformation matrix of the GN coordinate system based on the orthogonal coordinate system; calculate the increment of the stress component of the initial configuration data in a single orthogonal coordinate system; further calculate the stress in the fiber coordinate system at the current increment step, and then combine the transformation matrix to transform the stress in the orthogonal coordinate system to the GN coordinate system, and superimpose the total stress in the GN coordinate system to form a finite element calculation model;

[0009] Obtain the initial size of the two-dimensional fiber fabric, and use polar coordinates [θ k , r k to define the coordinates of the control points on the fabric boundary. Based on the kth control point P k on the fabric boundary, set the limiting condition r k of the radial distance |RP k | between the control point P k and the minimum boundary of the fabric; obtain the angular coordinates θ k of each control point P k , and sort the angular coordinates θ k of the control points generated by the optimization algorithm; then perform parametric "cutting" on the fabric grid with the initial size after sorting the angular coordinates θ k to obtain the "cut" fabric grid; simulate and calculate the deformation of the fabric material based on the finite element model to obtain the fabric strain distribution; then evaluate the severity of the forming defect based on the fabric strain distribution to obtain a parametric simulation and evaluation model for loading fabric shape control;

[0010] Load the parametric simulation and evaluation model for loading fabric shape control and output the maximum value of the absolute value of the principal direction compression strain of the fiber Initialize the polar coordinates [θ k , r k of the control points in the simulation and evaluation model, and determine the value range of the polar coordinates; then set the optimization objective and constraint conditions of the simulation and evaluation model in the Isight software based on the design goal, and select an optimization algorithm to perform running calculations until the optimal solution is obtained to complete the fabric shape parameter design.

[0011] Preferably, the orthogonal coordinate system is [e f1 , e f2 , e f3 and [e f1 , e f2 , e f3 , where the vector e fi is the contravariant vector of e fi . The calculation formula of the vector e fi is:

[0012]

[0013] e f3 is the unit vector perpendicular to the fabric plane. The calculation formula of e f3 is:

[0014]

[0015] Preferably, the calculation formula for the increment of the stress component under the single orthogonal coordinate system is:

[0016] where E f1 and E f2 are the moduli in the two main directions of the fiber respectively, and G 12 is the fabric shear modulus; and are the increments in different stress component directions; and are the stress components in different directions.

[0017] Preferably, the calculation formula for the transformation matrix is:

[0018]

[0019] where Q f1 and Q f2 are both transformation matrices, Q f1→GN and Q f2→GN are the two main fiber directions in the orthogonal coordinate system respectively, and g 1 , g 2 and g 3 are the three orthogonal directions in the orthogonal coordinate system respectively.

[0020] Preferably, the stress in the fiber coordinate system at the current increment step is obtained by superimposing the increment dσ fi of the stress component in the fiber coordinate system within the current increment step and the stress of the previous increment step. The calculation formula is:

[0021]

[0022] The calculation formula for converting the stress in the orthogonal coordinate system to the GN coordinate system is as follows:

[0023]

[0024] Preferably, the set point P k has its radial coordinate measured from the minimum boundary of the fabric, and the radial distance |RP k | between the point P k and the minimum boundary of the fabric is normalized to form the constraint condition r k ; the constraint condition r k is: r k ∈ [0, 1].

[0025] Preferably, the specific steps for parameterized "cutting" of the fabric mesh are as follows: retain the elements inside the polygon formed by connecting the control points, delete the elements outside it, and thus obtain the "cut" fabric mesh; use the maximum value of the absolute value of the compressive strain in the main direction of the fabric fibers in the fabric strain distribution to evaluate the severity of the forming defect.

[0026] Preferably, through the Variables option of the Optimisation component, initialize the polar coordinates [θ k , r k of the control points in the model; through the Objectives option of the Optimization component, set the optimization objective of the optimization model; through the Constraints option of the Optimization component, set the constraint conditions of the optimization model; through the General option of the Optimization component, select the optimization algorithm; select RunComponent to perform the running calculation.

[0027] The initial shape optimization and cutting method of the fabric preform based on finite element simulation in this application has the following advantages:

[0028] It can obtain the optimal solution of the fabric shape corresponding to the minimum value of the fabric forming defect characterization quantity through numerical simulation calculation, avoiding repeated trial and error based on a large number of fabric forming physical experiments, and can effectively save the process design time and cost; taking the fabric shape as the optimization design variable, it can save the material usage by setting the maximum fabric area constraint. Brief Description of the Drawings

[0029] In order to more clearly illustrate the technical solutions provided in this application, the drawings will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application.

[0030] Figure 1This is the overall optimization design flowchart of the present application;

[0031] Figure 2 This is a schematic diagram of the main fiber directions before and after the deformation of two-dimensional fabric fibers in the present application;

[0032] Figure 3 This is a schematic diagram of the parametric fabric boundary based on boundary control points in the present application;

[0033] Figure 4 This is a schematic diagram of the fabric grid construction method based on boundary polyline cutting in the present application;

[0034] Figure 5 This is the biaxial non-crimp microstructure diagram of the present application;

[0035] Figure 6 This is a schematic diagram of the finite element model for stamping forming of a hemispherical mold in the present application;

[0036] Figure 7 This is a schematic diagram of the finite element model for stamping forming of a hemispherical mold in the present application;

[0037] Figure 8 This is a schematic diagram of the optimized fabric shape boundary in the present application;

[0038] Figure 9 This is a schematic diagram of the distribution of the principal fiber direction compressive strain before and after fabric shape optimization in the present application. Detailed implementation manners

[0039] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0040] A method for optimizing the initial shape and cutting of a fabric preform based on finite element simulation, by designing the initial shape of a two-dimensional fabric and adjusting the strain distribution of the fabric after forming deformation, minimizing manufacturing defects, so as to achieve the purpose of improving the quality of the preform.

[0041] As Figure 1 shown, the method includes the following steps:

[0042] Step S100, a finite element calculation model for fabric forming based on non-orthogonal constitutive relations

[0043] Obtain the initial configuration data of the two-dimensional fiber fabric and input the values into the Abaqus platform; obtain the unit direction vectors in the initial configuration data, then construct an orthogonal coordinate system using the unit direction vectors, and calculate the transformation matrix of the GN coordinate system based on the orthogonal coordinate system; calculate the increment of the stress components of the initial configuration data in a single orthogonal coordinate system based on the GN coordinate system; calculate the stress in the fiber coordinate system of the current increment step based on the increment of the stress components in the single orthogonal coordinate system, then combine the transformation matrix to transform the stress in the orthogonal coordinate system to the GN coordinate system, and then superimpose the total stress in the GN coordinate system; form a finite element calculation model.

[0044] By embedding the hypoelastic non-orthogonal constitutive relationship describing the in-plane deformation of the two-dimensional fabric into the finite element model, the effective simulation of the forming deformation of the two-dimensional fabric is realized. The definition of the fiber principal direction is shown in Figure 2 , where 0 g α (α = 1, 2, 3) is the material coordinate system of the finite element integration points in Abaqus, which is also called the Green-Naghdi coordinate system, hereinafter referred to as the GN coordinate system.

[0045] Preferably, use the deformation gradient tensor F to obtain the unit direction vector e of the fiber in the current configuration fi , and the calculation formula is:

[0046]

[0047] In formula (1), is the unit direction vector of the fiber in the initial configuration, and the subscript i = 1, 2 represents the two principal directions of the fibers in the fabric.

[0048] Preferably, as Figure 2 , the orthogonal coordinate system is [e f1 , e f2 , e f3 and [e f1 , e f2 , e f3 , where the vector e fi is the contravariant vector of e fi , and the calculation formula of the vector e fi is:

[0049]

[0050] e f3 is the unit vector perpendicular to the fabric plane, and the calculation formula of e f3 is:

[0051]

[0052] Preferably, the calculation formula of the transformation matrix is:

[0053]

[0054] Among them, Q f1 and Q f2 are both transformation matrices, Q f1→GN and Q f2→GN are respectively two principal fiber directions in the orthogonal coordinate system, and g 1 , g 2 and g 3 are respectively three orthogonal directions in the orthogonal coordinate system.

[0055] Preferably, the calculation formula for the increment of the stress component in a single orthogonal coordinate system is:

[0056]

[0057] where E f1 and E f2 are respectively the moduli in the two principal fiber directions, and G 12 is the fabric shear modulus; and are the increments of different stress components; and are both stress components.

[0058] Preferably, the stress in the fiber coordinate system at the current increment step is obtained by superimposing the increment dσ fi of the stress component in the fiber coordinate system within the current increment step and the stress in the previous increment step, and the calculation formula is:

[0059]

[0060] The calculation formula for converting the stress in the orthogonal coordinate system to the GN coordinate system is:

[0061]

[0062] Step S200, the parametric forming simulation and evaluation model based on fabric shape control

[0063] To ensure that the fabric can completely cover the hemispherical mold after forming deformation, the minimum boundary R of the fabric needs to be set; at the same time, the size of the cut fabric should not exceed its initial size; based on this, the present application defines the boundary of the cut fabric by connecting discrete control points in a multi-segment straight line sequence. Therefore, the feasible region of the control point P k is the region enclosed between the initial boundary of the fabric and the minimum boundary of the fabric, as shown in Figure 3 .

[0064] Specifically: Obtain the initial size of the two-dimensional fiber fabric, and use polar coordinates [θk , r k Define the coordinates of the fabric boundary control points. Based on the k-th control point P on the fabric boundary k , set the control point P k The radial distance |RP| from the fabric minimum boundary k | with the limiting condition r k , such that the point P k always lies within the feasible region; Obtain the angular coordinates θ k of each control point P k , and then perform parametric "cutting" on the fabric mesh with the initial size after sorting the angular coordinates θ k to avoid self-intersection of the connected lines of the control points; Then use the Abaqus / Python platform to perform parametric "cutting" on the fabric mesh with the initial size to obtain the "cut" fabric mesh; Simulate the deformation of the fabric material based on the finite element model, submit it to the Abaqus platform for calculation to obtain the fabric strain distribution; Then evaluate the severity of the forming defect based on the fabric strain distribution to obtain a parametric simulation and evaluation model for the shape control of the loaded fabric.

[0065] The limiting condition r k is: r k ∈ [0, 1].

[0066] To ensure that the point P k always lies within the feasible region, set the radial coordinate of the point P k to be measured from the fabric minimum boundary, and normalize the radial distance |RP| k between the point P k and the fabric minimum boundary to form the limiting condition r k . The angular coordinate θ k is the angle between the connecting line oP k and the x-axis.

[0067] Preferably, the specific steps for parametric "cutting" of the fabric mesh are: retain the elements inside the polygon formed by connecting the control points, and delete the elements outside it, thereby obtaining the "cut" fabric mesh. In this application, the elements with all three nodes located within the boundary are regarded as the elements to be retained, and the rest are the elements to be deleted, as shown in Figure 4 .

[0068] Preferably, the maximum absolute value of the compressive strain in the main direction of the fabric fibers in the fabric strain distribution is used to evaluate the severity of the forming defect; that is the greater the probability of the occurrence of the forming defect, the worse the forming quality of the preform, and vice versa, the better its forming quality.

[0069] Step S300: Based on Isight software, customize the fabric shape optimization design process for suppressing surface forming defects

[0070] Specifically: Load the parametric simulation and evaluation model for fabric shape control in Isight software, and output the maximum value of the absolute value of the compression strain in the main fiber direction Initialize the polar coordinates [θ k , r k of the control points in the simulation and evaluation model, and determine the value range of the polar coordinates; then, based on the design objective, set the optimization objective and constraint conditions of the simulation and evaluation model in Isight software, and select an optimization algorithm to perform running calculations until the optimal solution is obtained to complete the fabric shape parameter design

[0071] Preferably, through the Variables option of the Optimisation component, initialize the polar coordinate [θ k , r k parameters of the control points in the model; through the Objectives option of the Optimization component, set the optimization objective of the optimization model; through the Constraints option of the Optimization component, set the constraint conditions of the optimization model; through the General option of the Optimization component, select the optimization algorithm; select RunComponent to perform running calculations

[0072] As a specific implementation method, the following takes the die pressing forming of a biaxial non-crimp fabric hemisphere mold as an example for specific illustration

[0073] As shown in Figure 5 , the biaxial non-crimp fabric is composed of two layers of straight fibers perpendicular to each other tied by stitches interspersed in the thickness direction, and the stitches form a 45° angle with the main fiber direction. The material property parameters in the finite element model are: the nominal modulus in the main fiber direction is 10 GPa, the areal weight is 440 g / m2, and the nominal thickness is 0.4 mm; the relationship between the in-plane shear force F NCF of the fabric and the shear strain γ 12 is non-linear, and the specific relationship is shown in Equation (10):

[0074]

[0075] Among them, F yarn rotation is the contribution of the in-plane rotation of the fiber bundle to the in-plane shear force of the fabric, and F stitch is the contribution of the stitch deformation to the in-plane shear force of the fabric

[0076] The die pressing forming configuration is shown in Figure 6, the in-plane boundary of the blank-holder tooling is square, with an in-plane size of 300 mm × 300 mm. Its center contains a circular through-hole with a radius of 52 mm, and the hole edge has a 6-mm chamfer to accommodate the stamping die and fabric material to pass through; the radius of the hemispherical stamping die is 50 mm, and the stamping stroke is 50 mm. The initial shape of the non-crimp fabric is a square of 300 mm × 300 m, clamped between the upper / lower blank-holder toolings, and the main direction of the fabric fibers forms a 45° angle with the straight edge of the blank-holder tooling.

[0077] The implementation process is as follows:

[0078] 1) According to the above fabric material property parameters, write the material user subroutine VUMAT based on the method in step S100.

[0079] 2) Establish a finite element model for fabric stamping forming based on the hemispherical die: The single-layer fabric is constructed using the membrane element M3D4R; the fabric model contains a total of 3600 elements, and the element size is 5 mm × 5 mm; the GeneralContact contact relationship is adopted between various components in the model, the friction coefficient between fabric-fabric is 0.36, and the friction coefficient between fabric-die is 0.2.

[0080] 3) Set the load boundary conditions: The downward blank-holder force is a uniform pressure, acting on the bottom surface of the lower blank-holder, with a magnitude of 12500 Pa, and the resultant force is approximately 1000 N.

[0081] 4) Set the displacement boundary conditions: Apply a 50-mm stamping displacement to the hemispherical die.

[0082] 5) Use the Isight software, follow the steps in the section of step S300, integrate the Optimisation and Simcode components, and establish an analysis framework as shown in Figure 7 to achieve the connection of the calculation programs.

[0083] 6) In the Simcode component, load the Abaqus / Python parametric modeling script file through the Input option, initialize the coordinates of the boundary control points as design variables; load the Abaqus execution file through the Command option; load the output file through the Output and read the calculation result data.

[0084] 7) In the Isight software, through the Variables option of the Optimisation component, check the variables corresponding to the control point coordinates to initialize the design variables, and set their value ranges, that is, θ k ∈[0, 2π], r k ∈[0, 1].

[0085] 8) The fiber compression strain is strongly correlated with the severity of fabric forming defects. Therefore, in this example, in the Objective option of the Optimisation component of Isight software, the maximum value of the absolute value of the compression strain in the main fiber direction of the fabric is selected. as the objective function, that is, by minimizing to minimize the fabric forming defects.

[0086] 9) In the General option of the Optimisation component of Isight software, select Multi-island Genetic Algorithm, that is, the multi-island genetic algorithm as the optimization algorithm.

[0087] 10) In Isight software, select RunComponent to run the optimization process, obtain the optimal solution, and complete the fabric shape design for suppressing forming defects.

[0088] Figure 8 The optimized fabric boundary shape and the distribution of control points are shown; Figure 9 The compression strain distribution in the main fiber direction of the fabric before and after optimization is compared. The magnitude and distribution area of the compression strain have been significantly reduced. Among them, the magnitude of the maximum compression strain has decreased by 12%, verifying the feasibility of this method.

[0089] In summary, the present application has the following advantages:

[0090] It can obtain the optimal solution of the fabric shape corresponding to the minimum value of the fabric forming defect characterization quantity through numerical simulation calculation, avoiding repeated trial and error based on a large number of fabric forming physical tests, and can effectively save the process design time and cost; taking the fabric shape as the optimization design variable, it can save the material usage by setting the maximum fabric area constraint.

[0091] Finally, it should be noted that: in the attached drawings of the disclosed embodiments of the present invention, only the structures related to the disclosed embodiments are involved. Other structures can refer to the general design. Without conflict, the same embodiment and different embodiments of the present invention can be combined with each other;

[0092] Finally: The above are only the preferred embodiments of the present invention and are not used to limit the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present invention shall be included within the protection scope of the present invention.

Claims

1. A method for optimizing the initial shape of a fabric preform based on finite element simulation, characterized in that: include: Obtain the initial configuration data of the two-dimensional fiber fabric and input the values ​​into the Abaqus platform; Obtain the unit direction vector in the initial configuration data, then use the unit direction vector to construct an orthogonal coordinate system, and calculate the transformation matrix of the GN coordinate system based on the orthogonal coordinate system; calculate the increment of the stress component of the initial configuration data in a single orthogonal coordinate system; Then the stress in the fiber coordinate system of the current incremental step is calculated, and then the stress in the orthogonal coordinate system is converted to the GN coordinate system by combining the transformation matrix, and the total stress in the GN coordinate system is superimposed to form a finite element calculation model; Get the initial size of the two-dimensional fiber fabric using polar coordinates [θ k , r k ] Define the coordinates of the fabric boundary control points based on the kth control point P on the fabric boundary k , set the control point P k Radial distance from the minimum edge of the fabric |RP k |Restrictions k ; Get each control point P k The angular coordinate θ k , the angular coordinates θ of the control points generated by the optimization algorithm k Sort; then the diagonal coordinate θ k The sorted fabric mesh with the initial size is parameterized "cut" to obtain a "cut" fabric mesh; The deformation of fabric material is simulated and calculated based on the finite element model to obtain the fabric strain distribution; Then, the severity of the forming defects is evaluated based on the fabric strain distribution, and a parameterized simulation and evaluation model for loading fabric shape control is obtained; Loading fabric shape control parameterized simulation and evaluation model, outputting the maximum absolute value of compressive strain in the main direction of the fiber The polar coordinates [θ k , r k ] Initialize and determine the value range of polar coordinates; then, based on the design goals, set the optimization goals and constraints of the simulation and evaluation model in the Isight software, and select the optimization algorithm to run the calculation until the optimal solution is obtained to complete the fabric shape parameter design.

2. The method for optimizing the initial shape of a fabric preform based on finite element simulation according to claim 1, characterized in that: The orthogonal coordinate system is [e f1 ,e f2 ,e f3 ] and [e f1 ,e f2 ,e f3 ], where the vector e fi for e fi The contravariant vector, vector e fi The calculation formula is: e f3 is the unit vector perpendicular to the fabric plane, e f3 The calculation formula is:

3. The method for optimizing the initial shape of a fabric preform based on finite element simulation according to claim 2, characterized in that: The calculation formula for the increment of the stress component in the single orthogonal coordinate system is: Where E f1 and E f2 are the moduli in the two main directions of the fiber, G 12 is the fabric shear modulus; and is the increment of different stress component directions; and are stress components in different directions.

4. The method for optimizing the initial shape of a fabric preform based on finite element simulation according to claim 2, characterized in that: The calculation formula of the conversion matrix is: Among them, Q f1 and Q f2 are transformation matrices, Q f1→GN and Q f2→GN They are the two main directions of the fiber in the orthogonal coordinate system, and g1, g2 and g3 are the three orthogonal directions in the orthogonal coordinate system.

5. The method for optimizing the initial shape of a fabric preform based on finite element simulation according to claim 4, characterized in that: The stress in the fiber coordinate system of the current incremental step is determined by the increment dσ of the stress component in the fiber coordinate system in the current incremental step. fi The stress of the previous increment is The calculation formula is: The calculation formula for converting the stress in the orthogonal coordinate system to the GN coordinate system is:

6. The method for optimizing the initial shape of a fabric preform based on finite element simulation according to claim 1, characterized in that: The set point P k The radial coordinates of the point P are measured from the minimum boundary of the fabric. k Radial distance from the minimum edge of the fabric |RP k |Regularization, forming constraints r k ; Restriction r k for: r k ∈[0, 1].

7. The method for optimizing the initial shape of a fabric preform based on finite element simulation according to claim 1, characterized in that: The specific steps of parameterized "clipping" of the fabric mesh are: retaining the cells inside the polygon obtained by connecting the control points, deleting the external cells, and then obtaining the "clipped" fabric mesh; using the maximum absolute value of the compressive strain in the main direction of the fabric fiber in the fabric strain distribution To evaluate the severity of forming defects.

8. The method for optimizing the initial shape of a fabric preform based on finite element simulation according to claim 1, characterized in that: The polar coordinates of the control points in the model [θ k , r k ]Parameter initialization; set the optimization target of the optimization model through the Objectives option of the Optimization component; set the constraints of the optimization model through the Constraints option of the Optimization component; select the optimization algorithm through the General option of the Optimization component; select RunComponent to run the calculation.

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