Mesh setting method, system, device and storage medium for aircraft tire model

Abstract

The application discloses a grid setting method, system, device and storage medium of an aviation tire model, and belongs to the technical field of computer graphics. The grid setting method of the aviation tire model comprises the following steps: determining stress distribution information of a triangular rubber in an aviation tire model; selecting a local encryption range from triangular grids of the aviation tire model according to the stress distribution information; setting triangular grids in the local encryption range as encryption units, and performing one or more grid encryption operations on the encryption units, so as to perform stress analysis on the aviation tire model. The application can realize grid encryption of the aviation tire model and improve stress analysis accuracy.

Description

Technical Field

[0001] This application relates to the field of computer graphics, and in particular to a method, system, device and storage medium for setting up a mesh for an aircraft tire model. Background Technology

[0002] As a complex elastomer structure, aircraft tires exhibit significant multi-scale characteristics. Their performance often changes nonlinearly with loading conditions and is influenced by numerous factors in the operating environment, making their design complex and challenging. Traditional research methods largely rely on trial and error for experimental feedback, which is time-consuming, costly, and inaccurate. Furthermore, harsh or extreme operating conditions and the coupling of complex factors are difficult to achieve experimentally.

[0003] To improve design accuracy in processes such as multi-scale feature optimization and process standard output for tires, the field typically optimizes multi-objective functions for the rubber components in complex and extreme operating conditions. In finite element analysis of aircraft tires, situations such as tire contact with the ground or localized stress concentrations may occur during rubber performance calculations. Dense mesh finite element analysis is required at these stress concentration locations. However, due to the large overall size of the mesh nodes or the incompatibility of the mesh shape and structure with the overall mesh re-division, the accuracy of stress analysis for aircraft tires remains low.

[0004] Therefore, how to refine the mesh of aircraft tire models and improve the accuracy of stress analysis is a technical problem that needs to be solved by those skilled in the art. Summary of the Invention

[0005] The purpose of this application is to provide a mesh setting method for an aircraft tire model, a mesh setting system for an aircraft tire model, a device, and a storage medium, which can realize mesh refinement of the aircraft tire model and improve the accuracy of stress analysis.

[0006] To address the aforementioned technical problems, this application provides a method for setting the mesh of an aircraft tire model, the method comprising:

[0007] Determine the stress distribution information of the triangular rubber in the aircraft tire model;

[0008] Based on the stress distribution information, a local refinement range is selected from the triangular mesh of the aircraft tire model;

[0009] The triangular mesh within the local encryption range is set as an encryption unit, and a mesh encryption operation is performed on the encryption unit in order to perform stress analysis on the aircraft tire model.

[0010] Optionally, after performing a mesh encryption operation on the encryption unit, the method further includes:

[0011] An optimization operation is performed on the angle-distorted units in the aircraft tire model after the mesh refinement operation is performed; wherein, the angle-distorted units are triangular meshes whose angles are not in a preset range.

[0012] Optionally, before selecting the local refinement range from the triangular mesh of the aircraft tire model based on the stress distribution information, the method further includes:

[0013] Based on the initial node information, triangular contour data, initial mesh length, and mesh density input by the user, the DISTMESH method is executed to perform a partitioning operation, resulting in multiple triangular meshes.

[0014] Optionally, a local refinement range can be selected from the triangular mesh of the aircraft tire model based on the stress distribution information, including:

[0015] Based on the stress distribution information, the N triangular meshes with the highest stress change rate in the aircraft tire model are set as the target meshes;

[0016] Set adjacent triangular meshes that share at least two edges with the target mesh as the new target mesh;

[0017] Set the area containing all the target meshes and the new target mesh as the local encryption range.

[0018] Optionally, based on the stress distribution information, the top N triangular meshes with the highest stress change rates in the aircraft tire model are set as the target mesh, including:

[0019] The absolute value of the stress difference between each triangular network and its adjacent triangular network in the aircraft tire model is calculated based on the stress distribution information, and the ranking of the stress change rate of the triangular network is determined based on the absolute value of the stress difference.

[0020] The top N triangular meshes with the highest stress change rate in the aircraft tire model are set as the target mesh.

[0021] Optionally, performing a grid encryption operation on the encryption unit includes:

[0022] Perform one or more grid encryption operations on the encryption unit according to user instructions.

[0023] Optionally, perform one or more grid encryption operations on the encryption unit according to user instructions, including:

[0024] Step 1: Perform N grid encryption operations on the encryption unit; where N≥1, and the value of N is determined according to the configuration information;

[0025] Step 2: Determine whether the user instruction has been received; if yes, proceed to Step 3; if no, determine that the grid encryption operation has been completed.

[0026] Step 3: Select a new local encryption range from the triangular mesh after performing the mesh encryption operation, and perform one or N mesh encryption operations on the encryption units in the new local encryption range, and then proceed to step 2.

[0027] Optionally, performing a grid encryption operation on the encryption unit includes:

[0028] The edge type of each edge of the encryption unit is determined; wherein, the edge type includes non-adjacent edge, first-type adjacent edge and second-type adjacent edge; the non-adjacent edge of the encryption unit is not shared with other encryption units or non-encryption units, the first-type adjacent edge of the encryption unit is shared with other encryption units, and the second-type adjacent edge of the encryption unit is shared with non-encryption units;

[0029] The target point corresponding to each edge of the encryption unit is determined according to a preset rule; wherein, the preset rule is: the target point corresponding to the non-adjacent edge is the midpoint of the non-adjacent edge, the target point corresponding to the first type of adjacent edge is the centroid of other encryption units that share the first type of adjacent edge, and the target point corresponding to the second type of adjacent edge is a preset vertex of the non-encryption unit that shares the second type of adjacent edge, wherein the preset vertex is a vertex of the non-encryption unit that is not on the second type of adjacent edge.

[0030] Determine the centroid of the encryption unit, and generate lines connecting the centroid of the encryption unit to the three vertices of the encryption unit and the three target points to obtain a new triangular mesh.

[0031] This application also provides a mesh setting system for an aircraft tire model, the system comprising:

[0032] The stress distribution determination module is used to determine the stress distribution information of the triangular rubber in the aircraft tire model;

[0033] The range selection module is used to select a local refinement range from the triangular mesh of the aircraft tire model based on the stress distribution information;

[0034] The mesh encryption module is used to set the triangular mesh within the local encryption range as encryption units and perform mesh encryption operations on the encryption units in order to perform stress analysis on the aircraft tire model.

[0035] This application also provides a storage medium storing a computer program thereon, which, when executed, implements the steps of the above-described method for setting the mesh of an aircraft tire model.

[0036] This application also provides an apparatus including a memory and a processor, wherein the memory stores a computer program, and the processor, when calling the computer program in the memory, implements the steps of the above-described mesh setting method for an aircraft tire model.

[0037] This application provides a mesh setting method for an aircraft tire model, comprising: determining the stress distribution information of triangular rubber in the aircraft tire model; selecting a local refinement range from the triangular mesh of the aircraft tire model according to the stress distribution information; setting the triangular mesh within the local refinement range as a refinement unit, and performing a mesh refinement operation on the refinement unit in order to perform stress analysis on the aircraft tire model.

[0038] This application selects a local refinement range from the triangular mesh based on the stress distribution information of the triangular rubber in the aircraft tire model, sets the triangular mesh within the local refinement range as refinement units, and performs mesh refinement operation on the refinement units. Then, stress analysis is performed on the aircraft tire model based on the refined mesh. The above scheme determines the local refinement range requiring mesh refinement based on stress distribution information and refines the triangular mesh within the local refinement range. This scheme does not require re-dividing the entire mesh, reducing the impact of mesh refinement operation on the mesh structure information. Therefore, this application can achieve mesh refinement of the aircraft tire model and improve the accuracy of stress analysis. This application also provides a mesh setting system, a storage medium, and a device for aircraft tire models, which have the above-mentioned beneficial effects, and will not be elaborated further here. Attached Figure Description

[0039] To more clearly illustrate the embodiments of this application, the accompanying drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0040] Figure 1 A flowchart illustrating a mesh setting method for an aircraft tire model provided in an embodiment of this application;

[0041] Figure 2 This is a schematic diagram illustrating a new target mesh setting principle provided in an embodiment of this application;

[0042] Figure 3 This is a schematic diagram of a grid encryption principle provided in an embodiment of this application;

[0043] Figure 4 This is an example diagram of a first type of grid encryption provided in the embodiments of this application;

[0044] Figure 5This is an example diagram of the second type of grid encryption provided in the embodiments of this application;

[0045] Figure 6 A flowchart illustrating adaptive mesh refinement in finite element performance calculation of aircraft tires, provided as an embodiment of this application;

[0046] Figure 7 A schematic diagram of a denser mesh region selected from the top 20% of the total stress variation rate of the triangular rubber of an aircraft tire, as provided in an embodiment of this application;

[0047] Figure 8 This is a magnified schematic diagram illustrating a method for performing a single encryption process on encrypted units within the same range of the entire encrypted area of ​​the triangular rubber of an aircraft tire, as provided in an embodiment of this application.

[0048] Figure 9 This is a schematic diagram illustrating the optimization of angular distortion units after densifying the triangular rubber of an aircraft tire, as provided in an embodiment of this application.

[0049] Figure 10 This is a schematic diagram of the structure of a mesh setting system for an aircraft tire model provided in an embodiment of this application. Detailed Implementation

[0050] To make the objectives, technical solutions, and advantages of the embodiments of this application clearer, the technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0051] Please see below. Figure 1 , Figure 1 A flowchart illustrating a mesh setting method for an aircraft tire model provided in an embodiment of this application.

[0052] Specific steps may include:

[0053] S101: Determine the stress distribution information of the triangular rubber in the aircraft tire model;

[0054] This embodiment can be applied to aircraft tire design devices, achieving high-precision stress analysis by rationally setting the mesh of the aircraft tire model. The stress distribution information of the triangular mesh can be pre-input by the user, i.e., the stress distribution information before the triangular mesh of the aircraft tire model is refined.

[0055] S102: Select a local refinement range from the triangular mesh of the aircraft tire model based on the stress distribution information;

[0056] In the aircraft tire model, the stress concentration locations need to be meshed. Specifically, this step can select the stress concentration areas as the local refinement range based on the distribution information of the triangular rubber mesh and the stress distribution information.

[0057] S103: Set the triangular mesh within the local encryption range as encryption unit, and perform mesh encryption operation on the encryption unit in order to perform stress analysis on the aircraft tire model.

[0058] Prior to this step, the DISTMESH method can be used to perform a partitioning operation based on the initial node information, triangular contour data, initial mesh length, and mesh density input by the user, resulting in multiple triangular meshes.

[0059] After determining the local mesh refinement range, the triangular meshes within this range can be set as refinement units. Then, corresponding mesh refinement operations can be performed on these units, resulting in a denser and more numerous distribution of triangular meshes within the local refinement range. Following the refinement operation, stress analysis can be performed on the aircraft tire model. Based on the stress analysis results, optimization of the tire's rubber structure and materials can be carried out.

[0060] This embodiment selects a local refinement range from the triangular mesh based on the stress distribution information of the triangular rubber in the aircraft tire model. The triangular meshes within this local refinement range are then set as refinement units, and a mesh refinement operation is performed on these units. Finally, stress analysis is conducted on the aircraft tire model based on the refined mesh. This scheme determines the local refinement range requiring mesh refinement based on stress distribution information and refines the triangular meshes within that range. This approach eliminates the need to re-divide the entire mesh, reducing the impact of mesh refinement on the mesh structure information. Therefore, this embodiment can achieve mesh refinement of the aircraft tire model and improve the accuracy of stress analysis.

[0061] As for Figure 1 In a further description of the corresponding embodiment, after performing a mesh encryption operation on the encryption unit, an optimization operation can also be performed on the angle distortion unit in the aircraft tire model after the mesh encryption operation is performed; wherein, the angle distortion unit is a triangular mesh whose angle is not in a preset range.

[0062] As a feasible implementation method, a local refinement range can be selected from the triangular mesh of the aircraft tire model in the following way: based on the stress distribution information, the triangular meshes with the top N stress change rates in the aircraft tire model are set as target meshes; adjacent triangular meshes with at least two sides shared with the target meshes are set as new target meshes; and the area where all the target meshes and the new target meshes are located is set as the local refinement range.

[0063] Please see Figure 2 , Figure 2 This is a schematic diagram illustrating a new target mesh setting principle provided in an embodiment of this application. In the diagram, A1, A2, and A3 are the target meshes; B1 is an adjacent triangular mesh with three sides shared by the target mesh; and B2 is an adjacent triangular mesh with two sides shared by the target mesh. Therefore, both B1 and B2 are new target meshes. Figure 2 The regions containing A1, A2, A3, B1, and B2 are local encryption ranges.

[0064] Furthermore, the top N triangular meshes with the highest stress change rate in the aircraft tire model can be set as target meshes in the following way: calculate the absolute value of the stress difference between each triangular mesh and its adjacent triangular mesh in the aircraft tire model based on the stress distribution information, determine the stress change rate ranking of the triangular meshes based on the absolute value of the stress difference, and set the top N triangular meshes with the highest stress change rate in the aircraft tire model as target meshes.

[0065] Furthermore, the local encryption range may include one or more single encryption ranges, and then encryption operations are performed on each single encryption range. Specifically, in this embodiment, the encryption unit may be subjected to one or more grid encryption operations according to user instructions. In this embodiment, the number of encryption operations may be determined according to user instructions, and then the encryption unit may be subjected to one or more grid encryption operations according to the number of encryption operations.

[0066] Specifically, the process of performing one or more grid encryption operations on the encryption unit according to user instructions is as follows:

[0067] Step 1: Perform N grid encryption operations on the encryption unit; where N≥1, and the value of N is determined according to the configuration information;

[0068] In this step, the number of times the mesh encryption operation is executed is determined according to the configuration information. For example, when N=1, this step performs a mesh encryption operation once for all encryption units; when N=2, this step performs a mesh encryption operation twice for all encryption units; and when N=3, this step performs a mesh encryption operation three times for all encryption units.

[0069] Step 2: Determine whether the user instruction has been received; if yes, proceed to Step 3; if no, determine that the grid encryption operation has been completed.

[0070] The aforementioned user commands can be commands issued by the user after the cause of the rapid stress change has not been determined, or commands issued when other meshing requirements have not been met; no specific limitations are made here.

[0071] Specifically, step 2 can be: determining whether the user instruction has been received within a preset time; if yes, proceed to step 3; if no, determine that the grid encryption operation has been completed and end the process.

[0072] Step 3: Select a new local encryption range from the triangular mesh after performing the mesh encryption operation, and perform one or N mesh encryption operations on the encryption units in the new local encryption range, and then proceed to step 2.

[0073] In step 3 above, if further encryption is required, one mesh encryption operation can be performed directly on the encryption units in the new local encryption range, or N mesh encryption operations can be performed on the encryption units in the new local encryption range according to the configuration information, so as to improve the flexibility of the encryption mesh process.

[0074] Furthermore, in this embodiment, all encrypted units can be subjected to a single mesh encryption operation. After performing the mesh encryption operation and stress analysis, the user command is used to determine whether the cause of rapid stress change is obtained. If the cause of rapid stress change is not obtained, the part with rapid stress change is selected again for mesh encryption operation based on the encrypted mesh.

[0075] Furthermore, the encryption unit can be encrypted in the above embodiments in the following ways:

[0076] (1) Determine the edge type of each edge of the encryption unit;

[0077] The edge types include non-adjacent edges, first-type adjacent edges, and second-type adjacent edges. The non-adjacent edges of an encryption unit are not shared with other encryption units or non-encryption units. The first-type adjacent edges of an encryption unit are shared with other encryption units, and the second-type adjacent edges of an encryption unit are shared with non-encryption units. A non-encryption unit refers to a triangular mesh that is not an encryption unit.

[0078] The aforementioned encryption unit may include any one or a combination of several of the following: non-adjacent edges, first-type adjacent edges, and second-type adjacent edges.

[0079] (2) Determine the target point corresponding to each edge of the encryption unit according to the preset rules;

[0080] The preset rules are as follows: the target point corresponding to the non-adjacent edge is the midpoint of the non-adjacent edge; the target point corresponding to the first type of adjacent edge is the centroid of other encryption units that share the first type of adjacent edge; the target point corresponding to the second type of adjacent edge is a preset vertex of the non-encryption unit that shares the second type of adjacent edge; and the preset vertex is a vertex in the non-encryption unit that is not on the second type of adjacent edge.

[0081] Please see Figure 3 , Figure 3 This is a schematic diagram illustrating the principle of target point determination provided in an embodiment of this application. Figure 3 In the diagram, A1, B1, C1, D1, E1, A2, B2, C2, D2, E2, F2, A3, B3, C3, D3, E3, and F3 represent the nodes of the triangular mesh; edge A1C1 is a non-adjacent edge, and the midpoint P1 of edge A1C1 is the target point; edge A2C2 is a first-type adjacent edge, and the centroid P2 of △A2C2F2 is the target point; edge A3C3 is a second-type adjacent edge, and the vertex F3 (i.e., P3) of △A3C3F3 is the target point.

[0082] (3) Determine the centroid of the encryption unit, generate lines connecting the centroid of the encryption unit to the three vertices of the encryption unit and the three target points respectively, and obtain a new triangular mesh.

[0083] The above method can ensure the integrity of the triangular mesh and prevent the triangular mesh from being destroyed, which may lead to errors in subsequent finite element calculations.

[0084] Please see Figure 4 , Figure 4 This is a first example diagram of mesh encryption provided in this application embodiment. In the diagram, △A4B4C4, △A4B4D4, △B4C4F4, and △A4C4E4 are encryption units, and O1, O2, O3, and O4 are the centroids corresponding to each encryption unit. In this embodiment, the centroid of the encryption unit can be determined, and lines can be drawn connecting the centroid of the encryption unit to the vertex of the encryption unit and the centroid of the adjacent encryption unit to obtain a new triangular mesh. Figure 4 The central triangle △A4B4C4 is divided into 6 triangles, thus achieving the encryption of the triangular mesh.

[0085] Please see Figure 5 , Figure 5This is an example diagram of the second type of mesh encryption provided in this application embodiment. In the diagram, △A5B5C5 and △A5B5D5 are encrypted units, △A5C5E5 is an unencrypted unit, △A5B5C5 has only two adjacent triangular meshes, O5 is the centroid of △A5B5C5, O6 is the centroid of △A5B5D5, and P5 is the midpoint of edge B5C5. The centroid O5 of the encrypted unit is connected to the centroids of A5, B5, C5, O6, E5, and P5 respectively to obtain a new triangular mesh. Figure 5 The central triangle △A5B5C5 is divided into 6 triangles, thus achieving the encryption of the triangular mesh.

[0086] To overcome the shortcomings and deficiencies of existing technologies, this embodiment proposes an adaptive mesh refinement method for finite element performance calculation of aircraft tires, which obtains an adaptive locally refined triangular mesh based on the rate of change of initial stress.

[0087] The above-mentioned scheme for achieving adaptive mesh refinement in the finite element performance calculation of aircraft tires is as follows:

[0088] Step 1: Calculate the initial stress of the aircraft tire model;

[0089] Specifically, this embodiment can use the finite element method to provide the mesh node information and stress distribution of the aircraft tire and its parts, and locally refine the triangular mesh according to the stress distribution while keeping the mesh of other parts unchanged.

[0090] Step 2: Select the local reinforcement range based on the stress distribution and actual engineering needs;

[0091] Specifically, this embodiment can identify and refine regions where the stress distribution change rate accounts for the top 5%, 10%, 20%, or 30% of the total change rate (i.e., regions of rapid stress change) based on engineering needs. After local refinement, the causes of rapid stress changes can be discussed, and the rubber structure and tire materials of the aircraft tire and its components can be optimized based on this.

[0092] Step 3: Filter out the encryption units within the same range, and use a loop to perform local encryption on each area of ​​all selected encryption grids;

[0093] Specifically, among all elements with large stress variation rates, the same range of densified elements is obtained based on the mesh information. That is, elements with shared edges are selected from all densified meshes. After obtaining the same range of densified elements, details are supplemented, and a single non-densified element surrounded by the densified elements is added as a densified element.

[0094] Step 4: Refine the mesh of the selected area once or multiple times according to the needs of the project and finite element calculation;

[0095] In this process, the centroid of the selected unit is connected to the three vertices and newly added nodes in the adjacent units. One unit is decomposed into six units. The original unit information is deleted from the total grid information, and the newly added units are added to the total grid information to form a new total grid unit. This is a local one-time encryption process within the same range. If the calculation needs are met, secondary or multiple encryption can be performed, that is, the encryption process is repeated in the already encrypted grid units to meet the calculation requirements.

[0096] Step 5: Optimize the angle distortion elements of all encrypted meshes to obtain the final node data and mesh element information.

[0097] Based on the above steps, local mesh refinement can be achieved while the remaining meshes retain their original structural characteristics. This embodiment optimizes angular distortion elements in all refined meshes to obtain final node data and mesh element information. Boundary elements and internal elements are discussed separately, with angular distortion cases processed iteratively. Angle distortion elements are defined as triangles with one interior angle less than or equal to 20° or greater than or equal to 125°.

[0098] This embodiment discloses an adaptive mesh refinement scheme for finite element performance calculations of aircraft tires. It can perform localized mesh refinement in areas with high stress variation rates while preserving the overall mesh characteristics in finite element calculations of tire contact problems and rubber structure optimization in aircraft tire components. This eliminates the need for complete mesh re-division, saving program execution time and preserving mesh structure information. This embodiment is not only applicable to finite element calculations in aircraft tires but can also be applied to any adaptive mesh refinement process based on stress variation rates.

[0099] Please see Figure 6 , Figure 6 The flowchart for adaptive mesh refinement in finite element performance calculation of aircraft tires provided in this application embodiment includes the following steps: calculating the initial stress of the model; selecting a local refinement range based on the stress distribution and actual engineering needs; filtering out refinement elements within the same range; deleting elements from the total refinement range to select the selected elements; refining the selected area mesh once or multiple times according to engineering and finite element calculation needs until the unrefined refinement elements are empty; optimizing angle-distorted elements in all refined meshes to obtain the final node data and mesh element information.

[0100] In this embodiment, the initial stress of the model is first calculated, and the mesh node information and stress distribution of the triangular rubber of the aircraft tire are given using the finite element method. Then, based on the stress distribution and actual engineering needs, a local refinement range is selected, and areas with large stress distribution change rates (i.e., areas of rapid stress change) are refined. Next, refinement elements within the same range are selected, and elements with shared edges are chosen from all elements with large stress distribution change rates based on the mesh information. Within the same local refinement area, the selected area mesh is refined once or multiple times according to engineering and finite element calculation needs. Then, a loop is used to locally refine each region of all selected refinement meshes, obtaining the refined mesh information and node information. Finally, angle-distorted elements are optimized in all refined meshes. Elements with angle distortion exist in all refined elements; these elements are discussed separately for boundary elements and internal elements, resulting in the final suitable node data and mesh element information.

[0101] Please see Figure 7 , Figure 7 This application provides a schematic diagram of a region where the stress change rate of the triangular rubber of an aircraft tire accounts for the top 20% of all change rates, thus requiring a finer mesh. Please refer to [link to relevant documentation]. Figure 8 , Figure 8 This is a magnified schematic diagram illustrating a method for performing a single encryption process on encrypted units within the same range of the entire encrypted area of ​​the triangular rubber of an aircraft tire, as provided in an embodiment of this application. Figure 7 and Figure 8 The region S with a larger grayscale value represents the mesh that does not require refinement, while the region S' with a smaller grayscale value represents the mesh that requires refinement (i.e., refinement cells). See also... Figure 9 , Figure 9 This is a schematic diagram illustrating the optimization of angular distortion units after densifying the triangular rubber of an aircraft tire, as provided in an embodiment of this application.

[0102] In specific implementation, the steps for calculating the initial stress of the model in the embodiment include:

[0103] The triangular mesh information is obtained using the DISTMESH method (a Matlab mesh generation program) based on the initial node information, the triangular rubber profile data of the aircraft tire, the initial mesh length, mesh density, and other information. Then, the stress distribution of the triangular rubber of the aircraft tire is given by the finite element method.

[0104] In specific implementation, the steps for selecting the local reinforcement range based on stress distribution and actual engineering needs in the above embodiments include:

[0105] This embodiment identifies regions where stress distribution changes account for 20% of all changes and refines them. The absolute values ​​of the stress differences between all elements and their three adjacent elements are obtained from the stress distribution and adjacent element information. The top 20% of these values ​​are selected as elements with high stress change rates and then refined within these ranges.

[0106] In specific implementation, the embodiment selects encryption units within the same range and performs local encryption on each region of all selected encryption grids using a loop. The specific steps include:

[0107] Among all elements with high stress variation rates, elements sharing common edges are selected based on the information of adjacent elements in the mesh as the same range of densified elements. After obtaining the densified elements within the same range, details are supplemented, and single non-densified elements surrounded by the densified elements are added as densified elements. Local densification is performed, and then the process is repeated to obtain the densification of all elements with high stress variation rates.

[0108] In specific implementation, the steps for refining the selected area mesh once or multiple times according to the needs of engineering and finite element calculations include:

[0109] Based on the engineering and finite element calculation requirements, this embodiment performs a local one-time densification of the selected area mesh for the triangular rubber of aviation tires. For each element in the selected area, the centroid and three vertices of the element are connected and connected to the newly added nodes in the adjacent elements. One element is decomposed into six elements. The original element information is deleted from the total mesh information, and the newly added elements are added to the total mesh information to form a new total mesh element. This is a local one-time densification process for the same range.

[0110] In specific implementation, the embodiment optimizes the angle distortion elements of all encrypted meshes to obtain the final node data and mesh element information. The specific steps include:

[0111] Let the angularly distorted elements be defined as triangles, with interior angles less than or equal to 20° or greater than or equal to 125°. First, handle angle distortions greater than 125°: calculate the angle of each node within the triangle element that is a vertex in the element, identify the location of the large-angle distorted node, and move the node to the centroid of the larger polygon formed by the elements sharing that node. If large-angle distortions still exist after readjustment, handle and optimize separately for internal and boundary elements. For boundary elements, move the distorted vertex to the midpoint of the other two nodes and delete the element. For internal elements, find the vertex with the smallest angle in the distorted element and merge it with the small-angle distorted point. For small-angle distorted elements, move the two nodes opposite the small-angle vertex of the triangle to the midpoint of that edge and delete the distorted element.

[0112] Please see Figure 10 , Figure 10This is a schematic diagram of the structure of a mesh setting system for an aircraft tire model provided in an embodiment of this application. The system may include:

[0113] The stress distribution determination module 801 is used to determine the stress distribution information of the triangular rubber in the aircraft tire model;

[0114] The range selection module 802 is used to select a local refinement range from the triangular mesh of the aircraft tire model according to the stress distribution information;

[0115] The mesh encryption module 803 is used to set the triangular mesh within the local encryption range as encryption units and perform mesh encryption operations on the encryption units in order to perform stress analysis on the aircraft tire model.

[0116] This embodiment selects a local refinement range from the triangular mesh based on the stress distribution information of the triangular rubber in the aircraft tire model. The triangular meshes within this local refinement range are then set as refinement units, and a mesh refinement operation is performed on these units. Finally, stress analysis is conducted on the aircraft tire model based on the refined mesh. This scheme determines the local refinement range requiring mesh refinement based on stress distribution information and refines the triangular meshes within that range. This approach eliminates the need to re-divide the entire mesh, reducing the impact of mesh refinement on the mesh structure information. Therefore, this embodiment can achieve mesh refinement of the aircraft tire model and improve the accuracy of stress analysis.

[0117] Furthermore, it also includes:

[0118] An angle distortion optimization module is used to perform an optimization operation on angle distortion units in the aircraft tire model after performing a mesh encryption operation on the encryption unit; wherein, the angle distortion unit is a triangular mesh whose angle is not in a preset range.

[0119] Furthermore, it also includes:

[0120] The triangular mesh generation module is used to perform a partitioning operation of the DISTMESH method based on the user-input initial node information, triangular rubber contour data, initial mesh length and mesh density before selecting a local refinement range from the triangular mesh of the aircraft tire model according to the stress distribution information, so as to obtain multiple triangular meshes.

[0121] Furthermore, the process by which the range selection module 802 selects a local refinement range from the triangular mesh of the aircraft tire model based on the stress distribution information includes: setting the top N triangular meshes in the aircraft tire model with the highest stress change rate as target meshes based on the stress distribution information; setting adjacent triangular meshes that share at least two sides with the target meshes as new target meshes; and setting the area where all the target meshes and the new target meshes are located as the local refinement range.

[0122] Furthermore, the process by which the range selection module 802 sets the top N triangular meshes in terms of stress change rate in the aircraft tire model as target meshes based on the stress distribution information includes: calculating the absolute value of the stress difference between each triangular mesh and its adjacent triangular mesh in the aircraft tire model based on the stress distribution information; determining the stress change rate ranking of the triangular mesh based on the absolute value of the stress difference; and setting the top N triangular meshes in terms of stress change rate in the aircraft tire model as target meshes.

[0123] Furthermore, the process by which the mesh encryption module 803 performs mesh encryption operations on the encryption unit includes: performing one or more mesh encryption operations on the encryption unit according to user instructions.

[0124] Furthermore, the process by which the mesh encryption module 803 performs one or more mesh encryption operations on the encryption unit according to user instructions includes:

[0125] Step 1: Perform N grid encryption operations on the encryption unit; where N≥1, and the value of N is determined according to the configuration information;

[0126] Step 2: Determine whether the user instruction has been received; if yes, proceed to Step 3; if no, determine that the grid encryption operation has been completed.

[0127] Step 3: Select a new local encryption range from the triangular mesh after performing the mesh encryption operation, and perform one or N mesh encryption operations on the encryption units in the new local encryption range, and then proceed to step 2.

[0128] Furthermore, the process by which the mesh encryption module 803 performs mesh encryption operation on the encryption unit includes: determining the edge type of each edge of the encryption unit; wherein the edge type includes non-adjacent edges, first-type adjacent edges, and second-type adjacent edges; the non-adjacent edges of the encryption unit are not shared with other encryption units or non-encryption units, the first-type adjacent edges of the encryption unit are shared with other encryption units, and the second-type adjacent edges of the encryption unit are shared with non-encryption units; determining the target point corresponding to each edge of the encryption unit according to a preset rule; wherein the preset rule is: the target point corresponding to the non-adjacent edge is the midpoint of the non-adjacent edge, the target point corresponding to the first-type adjacent edge is the centroid of other encryption units sharing the first-type adjacent edge, and the target point corresponding to the second-type adjacent edge is a preset vertex of the non-encryption unit sharing the second-type adjacent edge, wherein the preset vertex is a vertex in the non-encryption unit that is not on the second-type adjacent edge; determining the centroid of the encryption unit, generating lines connecting the centroid of the encryption unit to the three vertices of the encryption unit and the three target points respectively, to obtain a new triangular mesh.

[0129] Since the embodiments of the system part correspond to the embodiments of the method part, please refer to the description of the embodiments of the method part for the embodiments of the system part, and they will not be repeated here.

[0130] This application also provides a storage medium on which a computer program is stored, which, when executed, can perform the steps provided in the above embodiments. The storage medium may include various media capable of storing program code, such as a USB flash drive, a portable hard drive, a read-only memory (ROM), a random access memory (RAM), a magnetic disk, or an optical disk.

[0131] This application also provides an electronic device that may include a memory and a processor. The memory stores a computer program, and when the processor calls the computer program in the memory, it can implement the steps provided in the above embodiments. Of course, the electronic device may also include various network interfaces, power supplies, and other components.

[0132] The various embodiments in this specification are described in a progressive manner, with each embodiment focusing on its differences from other embodiments. Similar or identical parts between embodiments can be referred to interchangeably. For the systems disclosed in the embodiments, since they correspond to the methods disclosed in the embodiments, the descriptions are relatively simple; relevant parts can be referred to in the method section. It should be noted that those skilled in the art can make various improvements and modifications to this application without departing from the principles of this application, and these improvements and modifications also fall within the protection scope of the claims of this application.

[0133] It should also be noted that, in this specification, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

Claims

1. A method for setting up a mesh for an aircraft tire model, characterized in that, The method comprises the following steps: determining stress distribution information of the apex of an aviation tire model; selecting a local encryption range from the triangular mesh of the aviation tire model according to the stress distribution information; setting the triangular mesh in the local encryption range as an encryption unit, and performing a mesh encryption operation on the encryption unit, so as to perform stress analysis on the aviation tire model; wherein, selecting a local encryption range from the triangular mesh of the aviation tire model according to the stress distribution information comprises: setting the triangular mesh with the top N stress change rates in the aviation tire model as a target mesh according to the stress distribution information; setting the adjacent triangular mesh sharing at least two edges with the target mesh as a new target mesh; setting the area where all the target meshes and the new target meshes are located as the local encryption range; wherein, setting the triangular mesh with the top N stress change rates in the aviation tire model as a target mesh according to the stress distribution information comprises: calculating the absolute value of the stress difference between each triangular mesh and the adjacent triangular mesh in the aviation tire model according to the stress distribution information, and determining the stress change rate ranking of the triangular mesh according to the absolute value of the stress difference; setting the triangular mesh with the top N stress change rates in the aviation tire model as the target mesh.

2. The method of claim 1, wherein, After performing the mesh encryption operation on the encryption unit, the method further comprises: performing an optimization operation on the angle deformation unit in the aviation tire model after the mesh encryption operation; wherein, the angle deformation unit is a triangular mesh with an angle not in a preset interval.

3. The method of claim 1, wherein, Before selecting a local encryption range from the triangular mesh of the aviation tire model according to the stress distribution information, the method further comprises: performing a division operation of the DISTMESH method according to the initial node information, the apex contour data, the initial mesh length and the mesh density input by the user, to obtain a plurality of triangular meshes.

4. The method of claim 1, wherein, Performing a mesh encryption operation on the encryption unit comprises: performing 1 or more mesh encryption operations on the encryption unit according to the user instruction.

5. The method of claim 4, wherein, Performing 1 or more mesh encryption operations on the encryption unit according to the user instruction comprises: Step 1: performing N times of mesh encryption operations on the encryption unit; wherein, N≥1, and the value of N is determined according to the configuration information; Step 2: determining whether the user instruction is received; if yes, proceeding to Step 3; if no, determining that the mesh encryption operation is completed; Step 3: selecting a new local encryption range from the triangular mesh after the mesh encryption operation, and performing 1 or N times of mesh encryption operations on the encryption unit in the new local encryption range, and proceeding to Step 2.

6. The method of setting a grid for an aircraft tire model according to any one of claims 1 to 5, characterized in that, Performing a mesh encryption operation on the encryption unit comprises: determining the edge type of each edge of the encryption unit; wherein, the edge type comprises a non-adjacent edge, a first type of adjacent edge and a second type of adjacent edge; the non-adjacent edge of the encryption unit is not shared with other encryption units or non-encryption units, the first type of adjacent edge of the encryption unit is shared with other encryption units, and the second type of adjacent edge of the encryption unit is shared with non-encryption units; determining a target point corresponding to each edge of the encryption unit according to a preset rule, wherein the preset rule is that the target point corresponding to the non-adjacent edge is a midpoint of the non-adjacent edge, the target point corresponding to the first type of adjacent edge is a barycenter of other encryption units sharing the first type of adjacent edge, and the target point corresponding to the second type of adjacent edge is a preset vertex of a non-encryption unit sharing the second type of adjacent edge, the preset vertex being a vertex of the non-encryption unit not on the second type of adjacent edge; determining a barycenter of the encryption unit, generating a line connecting the barycenter of the encryption unit with three vertices of the encryption unit and three target points, and obtaining a new triangular mesh.

7. A meshing system for an aircraft tire model, characterized in that, Comprise: a stress distribution determination module configured to determine stress distribution information of the triangular rubber of the aircraft tire model; a range selection module configured to select a local encryption range from the triangular mesh of the aircraft tire model according to the stress distribution information; a mesh encryption module configured to set the triangular mesh in the local encryption range as an encryption unit, and perform a mesh encryption operation on the encryption unit to perform stress analysis on the aircraft tire model; The process of selecting a local encryption range from the triangular mesh of the aircraft tire model according to the stress distribution information by the range selection module comprises: setting triangular meshes with a top N stress change rate in the aircraft tire model as target meshes according to the stress distribution information; setting adjacent triangular meshes sharing at least two edges with the target meshes as new target meshes; and setting a region where all the target meshes and the new target meshes are located as the local encryption range; The process of setting triangular meshes with a top N stress change rate in the aircraft tire model as target meshes according to the stress distribution information by the range selection module comprises: calculating an absolute value of a stress difference between each triangular mesh and an adjacent triangular mesh in the aircraft tire model according to the stress distribution information, determining a stress change rate ranking of the triangular mesh according to the absolute value of the stress difference, and setting triangular meshes with a top N stress change rate in the aircraft tire model as the target meshes.

8. An apparatus, comprising: The memory and the processor, the memory stores a computer program, the processor calls the computer program in the memory to realize the steps of the grid setting method of the aircraft tire model in any one of claims 1 to 6.

9. A storage medium, characterized by The storage medium stores computer executable instructions, and the computer executable instructions are loaded and executed by the processor to realize the steps of the grid setting method of the aircraft tire model in any one of claims 1 to 6.

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