An analytical method for carbon fiber structures

Abstract

This invention discloses an analysis method for carbon fiber structures. The method includes: constructing a geometric model of a carbon fiber composite material using ANSYS Workbench software; setting material parameters for the carbon fiber composite material and meshing the geometric model to obtain a finite element mesh model; combining the layup parameters and reference direction set of the carbon fiber composite material with the ACP module to lay up the finite element mesh model to obtain a carbon fiber composite structural component; assembling the carbon fiber composite structural component with a solid element structure to obtain a carbon fiber composite assembly; analyzing and determining the structural response parameters of the carbon fiber composite assembly using a static structural analysis module in conjunction with the applied load location and boundary conditions; and optimizing and adjusting the structure of the carbon fiber composite material based on the structural response parameters. The carbon analysis method of this application can solve the problem of inaccurate analysis results caused by existing carbon fiber composite structure analysis methods not fully considering the material's structural characteristics.

Description

Technical Field

[0001] This invention relates to the field of carbon fiber technology, and more specifically, to a method for carbon fiber structural analysis. Background Technology

[0002] Carbon fiber composite structural components are widely used as both weight-reducing and reinforcing materials, making the verification of the layup strength and structural design of carbon fiber composites extremely important.

[0003] Currently, the structural strength analysis of carbon fiber composites mainly relies on empirical formulas and the manufacture of scaled-down components for analysis and verification. Alternatively, it involves finite element analysis of carbon fiber composites through secondary development based on the ANSYS APDL programming language (ANSYS parametric design language). The methods based on empirical formulas or manufactured scaled-down components primarily rely on simplified assumptions and averaged performance parameters, failing to comprehensively consider the structural characteristics of the material and making it difficult to accurately predict the performance of carbon fiber composite structural components under actual working conditions. While secondary development based on the ANSYS APDL programming language can form a relatively simple standard system, it has significant limitations and cannot handle complex material structural models.

[0004] In conclusion, there is an urgent need to provide an analytical method that can accurately and reliably analyze the structural strength of carbon fiber composites. Summary of the Invention

[0005] The main objective of this invention is to provide a carbon fiber structure analysis method to at least solve the problem that existing carbon fiber composite material structural strength analysis methods cannot fully consider the structural characteristics of the material, resulting in inaccurate analysis results.

[0006] According to one aspect of the present invention, a method for analyzing carbon fiber structures is provided, comprising:

[0007] Step S1: Construct a geometric model of the carbon fiber composite material using ANSYS Workbench software;

[0008] Step S2: Set the material parameters of the carbon fiber composite material and perform mesh generation on the geometric model to obtain a finite element mesh model;

[0009] Step S3: Combine the layup parameters and reference direction set of the carbon fiber composite material with the ACP module of ANSYS Workbench software to lay up the finite element network model to obtain the carbon fiber composite material structural component;

[0010] Step S4: Assemble the carbon fiber composite structural component with the solid unit structure to obtain a carbon fiber composite assembly;

[0011] Step S5: Analyze and determine the structural response parameters of the carbon fiber composite assembly using the static structural analysis module of ANSYS Workbench software, combined with the location of the applied load and boundary conditions.

[0012] Step S6: Optimize and adjust the structure of the carbon fiber composite material based on the structural response parameters.

[0013] Furthermore, the geometric model of the carbon fiber composite material is a two-dimensional thin-plate shell model, and step S1 includes:

[0014] Step S11: Perform a three-dimensional scan on the carbon fiber composite material to obtain a three-dimensional model of the carbon fiber composite material;

[0015] Step S12: Import the three-dimensional model of the carbon fiber composite material into ANSYS Workbench software in step format;

[0016] Step S13: Call the ACP module of the ANSYS Workbench software to convert the three-dimensional model of the carbon fiber composite material into a two-dimensional thin plate shell model based on the ACP module.

[0017] Further, the material parameters include material type, equivalent elastic modulus, Poisson's ratio, and shear modulus, and step S2 includes:

[0018] Step S21: Determine the material type of the carbon fiber composite material, and calculate the equivalent elastic modulus, Poisson's ratio, and shear modulus of the carbon fiber composite material based on Jones' mixing rule;

[0019] Step S22: Determine the mesh size and mesh density of the geometric model of the carbon fiber composite material based on the material type, equivalent elastic modulus, Poisson's ratio, and shear modulus;

[0020] Step S23: Combine the mesh size and mesh density to perform a meshing operation on the geometric model using 186 shell elements;

[0021] Step S24: Use the Multizone method to perform secondary meshing on the regions with curvature greater than the curvature threshold;

[0022] Step S25: Combine the results of the first mesh generation and the second mesh generation to determine the finite element mesh model of the geometric model of the carbon fiber composite material.

[0023] Further, step S3 includes:

[0024] Step S31: Determine the layup parameters and reference orientation set of the carbon fiber composite material;

[0025] Step S32: Import the ply parameters and reference direction set into the ACP module of ANSYS Workbench software;

[0026] Step S33: The ACP module combines the layup parameters and reference orientation set to create the corresponding composite material layer;

[0027] Step S34: Map the composite material layer to the corresponding region of the finite element network model to complete the laying of the composite material layer;

[0028] Step S35: Iteratively execute steps S33 to S34 until the required number of layup layers is reached to obtain a carbon fiber composite structural component.

[0029] Further, step S31 includes:

[0030] Step S311: Set the layup parameters and reference orientation set of the carbon fiber composite material according to the expected stress requirements of the carbon fiber composite material;

[0031] Step S312: Identify the anisotropic surface regions of the carbon fiber composite material and obtain the radius of curvature, shape changes, and position changes of the anisotropic surfaces;

[0032] Step S313: Adjust the layup parameters and reference direction set of the irregular surface of the carbon fiber composite material according to the curvature radius, shape change and position change.

[0033] Furthermore, the layup parameters include the number of layup layers, layup thickness, and layup angle, and the reference direction set includes the shell normal direction, layup direction, and layup fiber direction.

[0034] Further, step S4 includes:

[0035] Step S41: Determine the solid unit structure that matches the carbon fiber composite structural component;

[0036] Step S42: Construct the geometric model of the solid element structure and import it into ANSYS Workbench software;

[0037] Step S43: Determine the corresponding assembly relationship and set the corresponding assembly constraints based on the structural characteristics of the carbon fiber composite structural component and the structural characteristics of the solid unit structure;

[0038] Step S44: Based on the assembly relationship, the geometric model of the carbon fiber composite structural component and the solid unit structure is assembled using ANSYS Workbench software, and the assembly constraints are used to obtain the carbon fiber composite assembly.

[0039] Further, step S5 includes:

[0040] Step S51: Load the carbon fiber composite assembly into the static structural analysis module of ANSYS Workbench software;

[0041] Step S52: Based on the structural and functional characteristics of the carbon fiber composite assembly, set the location and boundary conditions for applying loads in the static structural analysis module;

[0042] Step S53: Analyze the carbon fiber composite assembly based on the applied load location and boundary conditions to obtain the structural response parameters corresponding to the carbon fiber composite assembly.

[0043] Furthermore, the structural response parameters include stress response, strain response, displacement response, and failure factor.

[0044] Further, the characteristic is that step S6 includes:

[0045] Step S61: Analyze the stress response, strain response, displacement response and failure factor respectively to determine the structural optimization target of the carbon fiber composite material;

[0046] Step S62: Adjust the layup parameters of the carbon fiber composite material based on the structural optimization objectives and re-import them into the ACP module of the ANSYS Workbench software;

[0047] Step S63: The ACP module re-lays the carbon fiber composite material to update the carbon fiber composite material structural component based on the adjusted layup parameters, and further updates the carbon fiber composite material assembly;

[0048] Step S64: Analyze the updated carbon fiber composite assembly and update the corresponding structural response parameters;

[0049] Step S65: Iteratively execute steps S61 to S64 until the obtained structural response parameters meet the structural response parameter threshold.

[0050] In this invention, carbon fiber composite materials are modeled and meshed using ANSYS Workbench software, enabling the construction of accurate and efficient finite element models and achieving finite element analysis of carbon fiber composite materials, significantly improving the accuracy of structural strength analysis. The ACP module is used for layup design of carbon fiber composite materials, fully considering layup parameters and reference direction sets, allowing for flexible handling of complex stress requirements and structural characteristics. By assembling carbon fiber composite structural components with solid element structures to form a complete assembly model, and comprehensively considering applied loads and boundary conditions in the static structural analysis module, the analysis results are closer to actual working conditions, helping to identify potential structural problems and collaboratively optimize overall structural performance. Through a comprehensive evaluation of structural response parameters, the performance characteristics and optimization directions of carbon fiber composite materials can be clearly defined, ensuring a balance between different performance indicators and resulting in a more reasonable structural design scheme. Attached Figure Description

[0051] The accompanying drawings, which are included to provide a further understanding of the invention and form part of this invention, illustrate exemplary embodiments of the invention and are used to explain the invention, but do not constitute an undue limitation of the invention. In the drawings:

[0052] Figure 1 This is a schematic flowchart of the fiber structure analysis method disclosed in an embodiment of the present invention. Detailed Implementation

[0053] It should be noted that, unless otherwise specified, the embodiments and features described in the present invention can be combined with each other. The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0054] It should be noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the scope of exemplary embodiments according to the invention. As used herein, the singular form is intended to include the plural form as well, unless the context clearly indicates otherwise. Furthermore, it should be understood that when the terms "comprising" and / or "including" are used in this specification, they indicate the presence of features, steps, operations, devices, components, and / or combinations thereof.

[0055] Unless otherwise specifically stated, the relative arrangement, numerical expressions, and values ​​of the components and steps set forth in these embodiments do not limit the scope of the invention. It should also be understood that, for ease of description, the dimensions of the various parts shown in the drawings are not drawn to actual scale. Techniques, methods, and devices known to those skilled in the art may not be discussed in detail, but where appropriate, such techniques, methods, and devices should be considered part of the specification. In all examples shown and discussed herein, any specific values ​​should be interpreted as merely exemplary and not as limitations. Therefore, other examples of exemplary embodiments may have different values. It should be noted that similar reference numerals and letters in the following figures denote similar items; therefore, once an item is defined in one figure, it need not be further discussed in subsequent figures.

[0056] In existing carbon fiber composite materials, structural strength analysis and verification are mainly based on empirical formulas or the manufacture of scaled-down parts. This approach fails to fully consider the structural characteristics of carbon fiber materials, resulting in inaccurate structural strength analyses. See [link to relevant documentation] for further information. Figure 1 As shown, according to an embodiment of this application, a carbon fiber structure analysis method is provided, comprising:

[0057] Step S1: Construct a geometric model of carbon fiber composite material based on ANSYS Workbench software.

[0058] Specifically, the geometric model of the carbon fiber composite material is a two-dimensional thin plate shell model, and step S1 includes:

[0059] Step S11: Perform a 3D scan on the carbon fiber composite material to obtain a 3D model of the carbon fiber composite material;

[0060] Step S12: Import the 3D model of the carbon fiber composite material into ANSYS Workbench software in step format;

[0061] Step S13: Call the ACP module of ANSYS Workbench software to convert the three-dimensional model of carbon fiber composite material into a two-dimensional thin plate shell model based on the ACP module.

[0062] This embodiment uses carbon fiber composite wing skin as an example to analyze the structure of carbon fiber composite materials. First, a 3D model of the carbon fiber composite material is acquired. This 3D model is obtained using a 3D scanner, including but not limited to handheld laser scanners and industrial-grade 3D measurement equipment. During scanning, the scanning environment is kept free of strong light sources, and the surface of the carbon fiber composite material is clean and unobstructed. The 3D scanner is aligned with the carbon fiber composite wing skin and scanned according to a preset scanning path. During the scanning process, an appropriate distance is maintained between the scanner and the material surface to avoid data loss or error accumulation. After scanning, the scanned data is imported into 3D modeling software for preprocessing to obtain a complete and accurate 3D model. Preprocessing includes at least noise reduction, hole repair, and surface smoothing. For example, 3D modeling software such as SolidWorks or CATIA can be used. In the 3D modeling software, the processed 3D model of the carbon fiber composite material is saved in STEP format. STEP format is a product model data exchange format under the ISO 10303 standard, a widely supported and highly standardized file format that ensures seamless transfer of the model between different software. ANSYS Workbench software is opened, a new project is created, and the "Geometry" module is selected in the project tree. In the "Geometry" module, click the "Import" button and select the STEP format file corresponding to the previously exported 3D carbon fiber composite model to import it into ANSYS Workbench. In the ANSYS Workbench project tree, locate and double-click the "ACP (ANSYS Composite PrepPost)" module to launch the composite material preprocessing module. In the ACP module, first identify and confirm that the imported 3D model is a carbon fiber composite wing skin. Then, use the "Shell from Solid" tool provided by the ACP module to convert the 3D model into a 2D thin-plate shell model. The ACP module will automatically calculate and generate the corresponding shell element mesh based on the geometric features and material properties of the 3D model to obtain the 2D thin-plate shell model.

[0063] In the above embodiments of this application, a three-dimensional model of the carbon fiber composite wing skin is obtained through high-precision three-dimensional scanning technology, and preprocessing is performed to ensure model quality. Then, a standardized format is used to achieve seamless model transfer. Finally, the ACP module of ANSYS Workbench is used to efficiently convert the three-dimensional model into a two-dimensional thin-plate shell model, providing an accurate data foundation for subsequent structural analysis and improving the reliability of the carbon fiber composite structure design.

[0064] Step S2: Set the material parameters of the carbon fiber composite material and mesh the geometric model to obtain a finite element mesh model.

[0065] Specifically, the material parameters include material type, equivalent elastic modulus, Poisson's ratio, and shear modulus. Step S2 includes:

[0066] Step S21: Determine the material type of the carbon fiber composite material, and calculate the equivalent elastic modulus, Poisson's ratio, and shear modulus of the carbon fiber composite material based on Jones' mixing rule;

[0067] Step S22: Determine the mesh size and mesh density of the geometric model of the carbon fiber composite material based on the material type, equivalent elastic modulus, Poisson's ratio, and shear modulus;

[0068] Step S23: Combine the mesh size and mesh density to perform a meshing operation on the geometric model using 186 shell elements;

[0069] Step S24: Use the Multizone method to perform secondary meshing on the regions where the curvature is greater than the curvature threshold;

[0070] Step S25: Combine the results of primary and secondary mesh generation to determine the finite element mesh model of the geometric model of carbon fiber composite material.

[0071] In this embodiment, the carbon fiber composite wing skin takes the commonly used carbon fiber / epoxy resin composite material in the aerospace field as an example. First, the equivalent elastic modulus, Poisson's ratio, and shear modulus of the carbon fiber composite material are calculated based on Jones' mixing rule. Assuming the longitudinal elastic modulus of carbon fiber is 230 GPa, the transverse elastic modulus is 10 GPa, the elastic modulus of epoxy resin is 3 GPa, and the volume fraction of carbon fiber in the composite material is 60%, the equivalent elastic modulus E of the carbon fiber composite material is calculated using Jones' mixing rule. c The calculation formula is as follows:

[0072] E c =E f V f +E m (1-V f );

[0073] In the formula: E f E represents the elastic modulus of carbon fiber. m V represents the elastic modulus of epoxy resin; f This indicates the volume fraction of carbon fiber.

[0074] Furthermore, the Poisson's ratio and shear modulus of carbon fiber / epoxy resin composites are related to the microstructure and fiber arrangement of the material. In this embodiment, a Poisson's ratio of 0.3 and a shear modulus of 8 GPa are assumed. The initial mesh size and mesh density are determined based on the specific equivalent elastic modulus, Poisson's ratio, and shear modulus. Higher equivalent elastic moduli correspond to carbon fiber / epoxy resin composites with stronger resistance to deformation under stress, requiring a finer mesh to accurately capture stress concentration and rapidly changing stress gradients. Poisson's ratio represents the ratio of transverse strain to longitudinal strain in the vertical direction when the carbon fiber / epoxy resin composite is subjected to uniaxial tension or expansion. It affects the distribution of stress and strain, thus affecting the accuracy of mesh generation; therefore, Poisson's ratio must be considered when generating the mesh. The shear modulus represents the ability of the carbon fiber / epoxy resin composite to resist shear deformation; a higher shear modulus also requires a finer mesh. Based on the obtained mesh size and density, Shell 186 elements were selected to mesh the geometric model of the carbon fiber / epoxy resin composite material. Shell 186 elements are suitable for analyzing thin-shell structures and can account for bending and shear effects. Regions with curvature greater than a preset threshold in the geometric model of the carbon fiber / epoxy resin composite material were identified. The ANSYS Multizone Meshing function was used to perform secondary meshing on these regions. The quality of the secondary meshing was controlled by setting local refinement parameters, and the analysis accuracy was improved by refining the mesh. Local refinement parameters included maximum mesh size, minimum mesh size, and mesh growth rate. The results of the primary and secondary meshing were combined to generate the final finite element mesh model.

[0075] In the embodiments described above in this application, the Jones mixture rule is employed, and by combining the material properties of carbon fiber and epoxy resin, the equivalent elastic modulus, Poisson's ratio, and shear modulus of carbon fiber composite materials can be accurately calculated. The calculation method of the Jones mixture rule can more accurately reflect the macroscopic mechanical properties of the composite material. Based on the equivalent elastic modulus, Poisson's ratio, and shear modulus of the carbon fiber composite material, a reasonable mesh size and mesh density can be determined, ensuring that the mesh generation can capture stress concentration and rapidly changing stress gradients while avoiding unnecessary waste of computational resources. Furthermore, by identifying regions with large curvature in the geometric model and performing secondary mesh generation, the accuracy and efficiency of mesh generation are further improved, especially in stress concentration regions, enabling more accurate simulation of the material's mechanical behavior.

[0076] Step S3: Combine the layup parameters and reference direction set of the carbon fiber composite material with the ACP module of ANSYS Workbench software to lay up the finite element network model to obtain the carbon fiber composite material structural component.

[0077] Specifically, the layup parameters include the number of layup layers, layup thickness, and layup angle, and the reference direction set includes the shell normal direction, layup direction, and layup fiber direction.

[0078] Specifically, step S3 includes:

[0079] Step S31: Determine the layup parameters and reference orientation set of the carbon fiber composite material.

[0080] Step S311: Set the layup parameters and reference direction set of the carbon fiber composite material according to the expected stress requirements of the carbon fiber composite material;

[0081] Step S312: Identify the anisotropic surface regions of the carbon fiber composite material and obtain the radius of curvature, shape changes, and position changes of the anisotropic surfaces;

[0082] Step S313: Adjust the layup parameters and reference orientation set of the irregular surface of the carbon fiber composite material according to the radius of curvature, shape change and position change.

[0083] Step S32: Import the layup parameters and reference direction set into the ACP module of the ANSYS Workbench software;

[0084] Step S33: The ACP module combines the layup parameters and reference orientation set to create the corresponding composite material layer;

[0085] Step S34: Map the composite material layer to the corresponding region of the finite element network model to complete the laying of the composite material layer;

[0086] Step S35: Iterate through steps S33 to S34 until the required number of layup layers is reached to obtain a carbon fiber composite structural component.

[0087] In this embodiment, the layup parameters of the carbon fiber / epoxy resin composite material are first set according to the expected stress requirements of the wing skin. These expected stress requirements include, for example, aerodynamic loads, bending, and torsion. For example, the layup parameters are: 16 layers, each 0.25 mm thick, and layup angles including 0° (along the wing span), ±45° (oblique reinforcement), and 90° (perpendicular to the wing span). Then, a reference direction set is determined, where the shell normal direction is the thickness direction of the wing skin (perpendicular to the surface), the layup direction is selected from the wing root to the wingtip, and the layup fiber direction is determined according to the layup angle. Irregular surface regions in the wing skin are identified. In this embodiment, irregular surface regions include, for example, the wingtip, wing root junction, and control surface mounting points. The radius of curvature, shape changes, and positional changes of these regions are obtained. Based on the radius of curvature, shape changes, and positional changes of the irregular surface regions, the layup parameters for these regions are adjusted. For example, increasing the number of layup layers or changing the layup angle at the wingtip can enhance local strength. In ANSYS Workbench, open the ACP module and import the previously created wing skin finite element model. Create a new composite layer definition, inputting equivalent values ​​for the carbon fiber / epoxy composite material, such as elastic modulus, Poisson's ratio, and shear modulus, as well as layup parameters and a reference direction set. The ACP module automatically generates the layup sequence and fiber orientation of the carbon fiber / epoxy composite material layers based on the input layup parameters and reference direction set. In the ACP module, select the "Map to Geometry" function to map the composite material layers onto the finite element mesh model of the wing skin, ensuring that the boundaries of the composite material layers perfectly match the geometric boundaries of the wing skin and that the layup orientation is correct. Lay up the composite material layer by layer until the predetermined number of layup layers (16 layers) is reached. After each layer is laid, check the layup quality to ensure there are no omissions, overlaps, or misalignments. After completing all layup layers, obtain the carbon fiber / epoxy composite material structural component and save it.

[0088] In the embodiments described above in this application, the ply parameters and reference direction set are set according to the expected stress requirements of the carbon fiber composite material, ensuring the scientific and rational nature of the ply design. Simultaneously, by identifying anisotropic regions and adjusting their ply parameters, the local strength and stiffness of the structural components are further enhanced, improving the overall load-bearing capacity and stability of the structure. Using the ACP module of ANSYS Workbench software, accurate mapping of ply parameters and reference direction sets to the finite element mesh model can be achieved. The ACP module can automatically generate the ply sequence and fiber orientation of the composite material layers, greatly reducing the complexity and error rate of manual operations.

[0089] Step S4: Assemble the carbon fiber composite structural components with the solid unit structure to obtain a carbon fiber composite assembly.

[0090] Specifically, step S4 includes:

[0091] Step S41: Determine the solid unit structure that matches the carbon fiber composite structural component;

[0092] Step S42: Construct the geometric model of the solid element structure and import it into ANSYS Workbench software;

[0093] Step S43: Determine the corresponding assembly relationship and set the corresponding assembly constraints based on the structural characteristics of the carbon fiber composite structural component and the solid unit structure;

[0094] Step S44: Based on the assembly relationship, the geometric model of the carbon fiber composite structural component and the solid element structure is assembled using ANSYS Workbench software, and the carbon fiber composite assembly is obtained by using assembly constraints.

[0095] In this embodiment, the function and position of the carbon fiber / epoxy resin composite structural component in the overall assembly are first determined, and the type of solid unit structure that needs to be matched with it is determined. In this embodiment, the solid unit structure includes, for example, a metal frame, support beams, and connectors. Based on the dimensions and interface requirements of the carbon fiber composite structural component, the dimensions and interfaces of the solid unit structure are determined to ensure a tight fit with the carbon fiber / epoxy resin composite structural component. Practical modeling software designs the geometric model of the solid unit structure based on its dimensions and structure. The obtained geometric model of the solid unit is saved in STEP format and then imported into ANSYS Workbench software via the "Import Geometry" option under the "File" menu. The assembly relationship between the carbon fiber / epoxy resin composite structural component and the solid unit structure is analyzed, including, for example, contact surfaces, connection points, and fit clearances. Based on the assembly relationship, corresponding assembly constraints are set in ANSYS Workbench. Assembly constraints include fixing constraints, contact constraints, and binding constraints. Fixing constraints are used to fix the structural component in a certain position to prevent it from moving. Contact constraints are used to simulate the contact behavior between two structural components, including normal contact and tangential friction. Binding constraints treat two structural components as a single unit, sharing nodes and degrees of freedom. In the Assembly module of ANSYS Workbench software, the carbon fiber composite structural components are assembled with the geometric model of the solid element structure according to the previously determined assembly relationships. During the assembly process, the corresponding structural components are constrained according to the set assembly constraints, resulting in a carbon fiber / epoxy composite assembly.

[0096] In the above embodiments of this application, by analyzing the assembly relationship between carbon fiber composite structural components and solid unit structures and setting corresponding assembly constraints, it can be ensured that the relative positions and contact states between various components are accurate during the assembly process, which helps to improve the overall stiffness, strength and durability of the assembly, thereby enhancing the overall structural strength of carbon fiber composite materials.

[0097] Step S5: Analyze and determine the structural response parameters of the carbon fiber composite assembly using the static structural analysis module of ANSYS Workbench software, combined with the location of the applied load and boundary conditions.

[0098] Specifically, the structural response parameters include stress response, strain response, displacement response, and failure factor. Step S5 includes:

[0099] Step S51: Load the carbon fiber composite assembly into the static structural analysis module of ANSYS Workbench software;

[0100] Step S52: Based on the structural and functional characteristics of the carbon fiber composite assembly, set the location and boundary conditions for applying loads in the static structural analysis module;

[0101] Step S53: Analyze the carbon fiber composite assembly based on the location of the applied load and the boundary conditions to obtain the structural response parameters corresponding to the carbon fiber composite assembly.

[0102] In this embodiment, the previously assembled carbon fiber / epoxy resin composite assembly is first imported into the "Static Structural" module of ANSYS Workbench software. Then, the locations and boundary conditions for applying loads are set. Since the composite material is wing skin, the applied loads include aerodynamic loads and gravitational loads. Aerodynamic loads are calculated based on flight speed and altitude and applied as distributed loads to the upper and lower surfaces of the carbon fiber / epoxy resin composite assembly (i.e., the upper and lower surfaces of the wing skin) to simulate aerodynamic pressure during flight. Gravity loads are applied by applying downward gravitational acceleration to the carbon fiber / epoxy resin composite assembly. The edges where stress boundaries need to be applied are determined, and the corresponding stress distribution functions are input into the static structural analysis module. After configuring all boundary conditions, the static structural analysis is run, using these boundary conditions to solve for the stress response, strain response, displacement response, and failure factor of the carbon fiber / epoxy resin composite assembly.

[0103] Step S6: Optimize and adjust the structure of the carbon fiber composite material based on the structural response parameters.

[0104] Specifically, step S6 includes:

[0105] Step S61: Analyze the stress response, strain response, displacement response and failure factor respectively to determine the structural optimization target of carbon fiber composite material;

[0106] Step S62: Adjust the layup parameters of the carbon fiber composite material based on the structural optimization objectives and re-import them into the ACP module of the ANSYS Workbench software;

[0107] Step S63: The ACP module re-lays the carbon fiber composite material based on the adjusted layup parameters to update the carbon fiber composite material structural components and further updates the carbon fiber composite material assembly;

[0108] Step S64: Analyze the updated carbon fiber composite assembly and update the corresponding structural response parameters;

[0109] Step S65: Iteratively execute steps S61 to S64 until the obtained structural response parameters meet the structural response parameter threshold.

[0110] In this embodiment, the stress response, strain response, and displacement response parameters in the structural response are first converted into stress response distribution maps, strain response distribution maps, and displacement response distribution maps, respectively. The location and stress concentration of high-stress areas are analyzed based on the stress response distribution maps to determine if the risk of exceeding the strength limit of the carbon fiber / epoxy resin composite material is present. High-strain areas are identified based on the strain response distribution maps, and the area and strain value of these areas are assessed to determine if they exceed preset values. If they do, there is a risk of affecting the structural integrity of the carbon fiber / epoxy resin composite material. The displacement response distribution maps are used to determine if the structure of the carbon fiber / epoxy resin composite material is within acceptable limits under predetermined working conditions. Potential failure areas are identified based on the distribution of failure factors. Corresponding structural optimization objectives are set based on the analysis of stress response, strain response, displacement response, and failure factors, such as reducing maximum stress, reducing strain concentration, and controlling displacement. The layup angle and layup thickness of the carbon fiber / epoxy resin composite material are adjusted according to the structural optimization objectives. For example, for high-stress areas, the layup thickness can be increased or the layup angle changed to disperse stress. The carbon fiber / epoxy resin composite material is re-layed and assembled based on the adjusted layup parameters, updating the carbon fiber / epoxy resin composite material assembly. The structural response parameters of the updated carbon fiber / epoxy resin composite assembly are re-analyzed to determine whether they all meet the structural response parameter thresholds. If they do, the analysis results are output; otherwise, the layup parameters are adjusted and the layup and assembly are repeated until the structural response parameters meet the structural response parameter thresholds.

[0111] In the above embodiments of this application, by analyzing the structural response parameters such as stress, strain, displacement and failure factor of carbon fiber composite materials, setting optimization targets and adjusting ply parameters, and using ANSYS Workbench software to realize ply updates and assembly optimization, the structural performance of carbon fiber composite materials is significantly improved, material costs are reduced, design efficiency and reliability are improved, and the stability and safety of carbon fiber composite material structures under predetermined working conditions are ensured.

[0112] For ease of description, spatial relative terms such as "above," "on top of," "on the upper surface of," "above," etc., are used herein to describe the spatial positional relationship of a device or feature as shown in the figures to other devices or features. It should be understood that spatial relative terms are intended to encompass different orientations in use or operation beyond the orientation of the device as described in the figures. For example, if the device in the figures were inverted, a device described as "above" or "on top of" other devices or structures would subsequently be positioned as "below" or "under" other devices or structures. Thus, the exemplary term "above" can include both "above" and "below." The device may also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatial relative descriptions used herein will be interpreted accordingly.

[0113] Furthermore, it should be noted that the use of terms such as "first" and "second" to define components is merely for the purpose of distinguishing the corresponding components. Unless otherwise stated, the above terms have no special meaning and therefore should not be construed as limiting the scope of protection of this invention.

[0114] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A method for analyzing carbon fiber structures, characterized in that, include: Step S1: Construct a geometric model of the carbon fiber composite material using ANSYS Workbench software; Step S2: Set the material parameters of the carbon fiber composite material and perform mesh generation on the geometric model of the carbon fiber composite material to obtain a finite element mesh model; Step S3: Combine the layup parameters and reference direction set of the carbon fiber composite material with the ACP module of ANSYS Workbench software to lay up the finite element mesh model to obtain the carbon fiber composite material structural component; Step S3 includes: Step S31: Determine the layup parameters and reference orientation set of the carbon fiber composite material; Step S311: Set the layup parameters and reference orientation set of the carbon fiber composite material according to the expected stress requirements of the carbon fiber composite material; Step S312: Identify the irregular surface region of the carbon fiber composite material and obtain the radius of curvature, shape change, and position change of the irregular surface; Step S313: Adjust the layup parameters and reference orientation set of the irregular surface of the carbon fiber composite material according to the radius of curvature, shape change and position change; Step S32: Import the ply parameters and reference direction set into the ACP module of ANSYS Workbench software; Step S33: The ACP module combines the layup parameters and reference orientation set to create the corresponding composite material layer; Step S34: Map the composite material layer to the corresponding region of the finite element mesh model to complete the laying of the composite material layer; Step S35: Iteratively execute steps S33 to S34 until the required number of layup layers is reached to obtain a carbon fiber composite structural component; Step S4: Assemble the carbon fiber composite structural component with the solid unit structure to obtain a carbon fiber composite assembly; Step S5: Analyze and determine the structural response parameters of the carbon fiber composite assembly using the static structural analysis module of ANSYS Workbench software, combined with the location of the applied load and boundary conditions. Step S6: Optimize and adjust the structure of the carbon fiber composite material based on the structural response parameters.

2. The analytical method for carbon fiber structures according to claim 1, characterized in that, The geometric model of the carbon fiber composite material is a two-dimensional thin plate shell model, and step S1 includes: Step S11: Perform a three-dimensional scan on the carbon fiber composite material to obtain a three-dimensional model of the carbon fiber composite material; Step S12: Import the three-dimensional model of the carbon fiber composite material into ANSYS Workbench software in step format; Step S13: Call the ACP module of the ANSYS Workbench software to convert the three-dimensional model of the carbon fiber composite material into a two-dimensional thin plate shell model based on the ACP module.

3. The analytical method for carbon fiber structures according to claim 2, characterized in that, The material parameters include material type, equivalent elastic modulus, Poisson's ratio, and shear modulus. Step S2 includes: Step S21: Determine the material type of the carbon fiber composite material, and calculate the equivalent elastic modulus, Poisson's ratio, and shear modulus of the carbon fiber composite material based on Jones' mixing rule; Step S22: Determine the mesh size and mesh density of the geometric model of the carbon fiber composite material based on the material type, equivalent elastic modulus, Poisson's ratio, and shear modulus; Step S23: Combine the mesh size and mesh density to perform a meshing operation on the geometric model using 186 shell elements; Step S24: Use the Multizone method to perform secondary meshing on the regions with curvature greater than the curvature threshold; Step S25: Determine the finite element mesh model of the geometric model of the carbon fiber composite material by combining the results of the first mesh generation and the second mesh generation.

4. The analytical method for carbon fiber structures according to claim 1, characterized in that, The layup parameters include the number of layup layers, layup thickness, and layup angle, and the reference direction set includes the shell normal direction, layup direction, and layup fiber direction.

5. The analytical method for carbon fiber structures according to claim 1, characterized in that, Step S4 includes: Step S41: Determine the solid unit structure that matches the carbon fiber composite structural component; Step S42: Construct the geometric model of the solid element structure and import it into ANSYS Workbench software; Step S43: Determine the corresponding assembly relationship and set the corresponding assembly constraints based on the structural characteristics of the carbon fiber composite structural component and the structural characteristics of the solid unit structure; Step S44: Based on the assembly relationship, the geometric model of the carbon fiber composite structural component and the solid unit structure is assembled using ANSYS Workbench software, and the assembly constraints are used to obtain the carbon fiber composite assembly.

6. The analytical method for carbon fiber structures according to claim 1, characterized in that, Step S5 includes: Step S51: Load the carbon fiber composite assembly into the static structural analysis module of ANSYS Workbench software; Step S52: Based on the structural and functional characteristics of the carbon fiber composite assembly, set the location and boundary conditions for applying loads in the static structural analysis module; Step S53: Analyze the carbon fiber composite assembly based on the applied load location and boundary conditions to obtain the structural response parameters corresponding to the carbon fiber composite assembly.

7. The analytical method for carbon fiber structures according to claim 6, characterized in that, The structural response parameters include stress response, strain response, displacement response, and failure factor.

8. The analytical method for carbon fiber structures according to claim 7, characterized in that, Step S6 includes: Step S61: Analyze the stress response, strain response, displacement response and failure factor respectively to determine the structural optimization target of the carbon fiber composite material; Step S62: Adjust the layup parameters of the carbon fiber composite material based on the structural optimization objectives and re-import them into the ACP module of the ANSYS Workbench software; Step S63: The ACP module re-lays the carbon fiber composite material to update the carbon fiber composite material structural component based on the adjusted layup parameters, and further updates the carbon fiber composite material assembly; Step S64: Analyze the updated carbon fiber composite assembly and update the corresponding structural response parameters; Step S65: Iteratively execute steps S61 to S64 until the obtained structural response parameters meet the structural response parameter threshold.

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