Composite material laying layer loss design and finite element modeling method

Abstract

The invention relates to the technical field of computer simulation, in particular to a composite material laying layer loss design and finite element modeling method, which comprises the following steps of S1, acquiring geometric profiles and laying layer information of all laying layer areas of a composite material part through a CATIA interface, and storing the geometric profiles and the laying layer information as an area list; and S2, by using the CATIA geometric processing capability and the interface, quickly geometrically generating a layer laying and layer losing line in the areas, and realizing the display of layer laying and layer losing. According to the method, by utilizing the interface capacity of CATIA and HyperMesh, information reading of a composite material laying layer area, automatic generation and display of a layer loss line and automatic creation of a finite element model are achieved, the problems of low efficiency and poor accuracy in traditional design modeling are effectively solved, composite material laying layer loss design and finite element modeling can be rapidly and accurately completed, and the method is suitable for large-scale popularization and application. And the quality and efficiency of the composite material structure design are obviously improved.

Description

Technical Field

[0001] The present invention relates to the technical field of computer simulation, and specifically provides a method for ply omission design and finite element modeling of composite materials. Background Art

[0002] In modern fields such as aerospace and automotive industries, composite materials have been widely used due to their advantages of high specific strength, high specific modulus, and strong designability. In the process of composite material structure design, ply design is one of the key links, and a reasonable ply design can fully exert the performance advantages of composite materials. However, under some complex structures or special design requirements, ply omission design is required, that is, some plies are reduced or cancelled in some areas to meet requirements such as weight reduction and stiffness adjustment. Currently, for the ply omission design and finite element modeling of composite materials, the following problems mainly exist: First, when performing ply omission design, there is a lack of systematic and efficient design methods, and the design process often relies on the experience of engineers, resulting in low design efficiency and difficulty in ensuring the accuracy and rationality of the design; second, in terms of finite element modeling, the model processing for the ply omitted structure is not precise enough, and it is impossible to accurately simulate the mechanical properties of the composite material structure after ply omission, resulting in a large deviation between the finite element analysis results and the actual situation, which affects the optimization design and performance evaluation of the composite material structure.

[0003] Based on this, the present invention provides a method for ply omission design and finite element modeling of composite materials to solve the above-mentioned technical problems. Summary of the Invention

[0004] The purpose of the present invention is to provide a method for ply omission design and finite element modeling of composite materials. By using the interface capabilities of CATIA and HyperMesh, the present invention realizes the reading of ply area information of composite materials, the automatic generation and display of ply omission lines, and the automatic creation of finite element models, effectively solving the problems of low efficiency and poor accuracy in traditional design modeling, and being able to quickly and accurately complete the ply omission design and finite element modeling of composite materials, significantly improving the quality and efficiency of composite material structure design.

[0005] To achieve the above purpose, the present invention provides the following technical solutions: The present invention provides a method for ply omission design and finite element modeling of composite materials, including the following steps: S1: Obtain the geometric surfaces and ply information of all ply areas of the composite material part through the CATIA interface and store them as a region list; S2: Use the CATIA geometric processing capabilities and interfaces to quickly generate ply omission lines on these regional geometries to realize the display of ply omission; S3: Starting from the second ply area, repeat step S2 until the ply drop lines for all ply areas are generated; S4: By utilizing the HyperMesh meshing capabilities and interfaces, import the CATIA composite part and ply drop data into HyperMesh, automatically complete meshing, ply property creation, and material coordinate system adjustment to generate a finite element model.

[0006] The composite part in S1 includes wing skins in the aerospace field, fuselage frames, and lightweight components in the automotive industry.

[0007] The ply information stored in S1 includes ply sequence, ply angle, ply thickness, and material type, and is stored in the area list in XML or JSON format.

[0008] The ply drop lines generated in S2 are differentiated by different colors for different ply angles in the CATIA graphics window, the line width is set to 0.3 - 0.5 mm, and the ply drop position is determined by the ply drop information generation algorithm.

[0009] The generation of ply drop information in S2 is as follows: S2.1: Obtain the number of plies in the current ply area and find all its adjacent areas; S2.2: Compare the number of plies in area A with that in adjacent area B. If the number of plies in area A is greater than that in area B, perform ply drop design.

[0010] The algorithm for finding adjacent areas in S2.1 is as follows: S3.1: The total number of ply areas is N. Starting from the first ply area, denote it as A; S3.2: The initial value of X is 1; S3.3: Find the Xth area in the area list and denote it as B; S3.4: When X ≤ N, compare whether A and B are the same. If A and B are the same, increment the value of X by 1 and re - execute step S3.3; S3.5: If A and B are not the same, find the intersection line between area A and B; S3.6: If the intersection line exists, then area B is an adjacent area of area A and is added to the adjacent area list of area A; S3.7: If the intersection line does not exist, increment the value of X by 1 and re - execute step S3.3; S3.8: Increment the value of X by 1 and re - execute step S3.3; S3.9: When X > N, exit.

[0011] The ply drop design algorithm in S2.2 is as follows: S2.2.1: The total number of plies is N, that is, the ply numbers are 1, 2, ……, N; S2.2.2: Select the ply number i, with the initial value being 1; S2.2.3: Judge the magnitude relationship between i and N; S2.2.4: If i ≤ N, obtain the ply with the number i in region A; S2.2.5: If the ply i in region A exists, obtain the ply with the number i in region B; S2.2.6: If the ply i in region A does not exist, then i + 1, and start from step S2.2.3 again; S2.2.7: If the ply i in region B exists, then i + 1, and start from step S2.2.3 again; S2.2.8: If the ply i in region B does not exist, find the intersection line of region A and region B as the static boundary line; S2.2.9: Input the starting offset o and the layer skipping distance d; S2.2.10: Offset the static boundary line into region B, and the offset distance is: , as the layer skipping line; S2.2.11: i + 1, and start from step S2.2.3 again; S2.2.12: If i > N, the layer skipping information creation of the ply region is completed.

[0012] In the above S4, by using the HyperMesh mesh processing capabilities and interfaces, the CATIA composite part and the layer skipping data are imported into HyperMesh, and the mesh generation, ply property creation, and material coordinate system adjustment are automatically completed to generate a finite element model. The specific steps are as follows: S4.1: Call the HyperMesh interface to import the finite element model; S4.2: Select the file output by CATIA for parsing, record the boundary point coordinates and the coordinates within each layer skipping region, and store them as dictionary A; S4.3: Loop through the obtained region information dictionary A, and according to the spatial coordinates, match the elements of each region in the finite element model and store them as dictionary B. The dictionary Key values are consistent with those of dictionary A; S4.4: Parse the ply information of each region, obtain the actual ply sequence, ply thickness, and ply material information in each ply, and store them as dictionary C. The dictionary Key values are consistent with those of dictionary A; S4.5: Perform loop processing on dictionary C, obtain the corresponding mesh information of the region from dictionary B through the Key value, and then create PCOMP according to the ply parameters in dictionary C and assign the created PCOMP attributes to the corresponding meshes; S4.6: Re-adjust the 0-degree direction of the material of the element according to the coordinate system of the designed ply. S4.7: Complete the assignment of all area attributes and implement the ply mapping operation.

[0013] Compared with the prior art, the beneficial effects of the present invention are as follows: By utilizing the interface capabilities of CATIA and HyperMesh, the present invention realizes the reading of composite ply area information, the automatic generation and display of ply-drop lines, and the automatic creation of a finite element model, effectively solving the problems of low efficiency and poor accuracy in traditional design modeling. It can quickly and accurately complete the ply-drop design of composites and finite element modeling, significantly improving the quality and efficiency of composite structure design. Description of the Drawings

[0014] Figure 1 It is a system flow chart of a method for composite ply-drop design and finite element modeling of the present invention.

[0015] Figure 2 It is an algorithm flow chart of adjacent regions in a method for composite ply-drop design and finite element modeling of the present invention.

[0016] Figure 3 It is an algorithm flow chart of ply-drop design in a method for composite ply-drop design and finite element modeling of the present invention.

[0017] Figure 4 It is a finite element modeling flow chart in a method for composite ply-drop design and finite element modeling of the present invention.

[0018] Figure 5 It is a ply area diagram of a composite part in a method for composite ply-drop design and finite element modeling of the present invention.

[0019] Figure 6 It is a ply-drop design diagram of each region and its adjacent regions in a method for composite ply-drop design and finite element modeling of the present invention.

[0020] Figure 7 It is a ply-drop diagram of the tail section of an aircraft wing in a method for composite ply-drop design and finite element modeling of the present invention. Detailed Embodiments

[0021] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without making creative efforts belong to the scope of protection of the present invention.

[0022] Embodiment: As Figures 1-7 shown, this embodiment provides a method for delamination design and finite element modeling of composite material laminates, including the following steps: S1: Obtain the geometric surfaces and ply information of all ply regions of the composite material part through the CATIA interface, and store them as a region list; S2: Utilize the CATIA geometric processing capabilities and interfaces to quickly generate delamination lines on these regional geometries to achieve the display of delamination; S3: Starting from the second ply region, repeat step S2 until the delamination lines of all ply regions are generated; S4: By utilizing the HyperMesh mesh processing capabilities and interfaces, import the CATIA composite material part and delamination data into HyperMesh, automatically complete mesh generation, ply property creation, and material coordinate system adjustment to generate a finite element model.

[0023] The composite material part in S1 includes wing skins, fuselage frames in the aerospace field, and lightweight components in the automotive industry.

[0024] The ply information stored in S1 includes ply sequence, ply angle, ply thickness, and material type, and is stored in the region list in XML or JSON format.

[0025] The delamination lines generated in S2 are distinguished by different colors for different ply angles in the CATIA graphics window, the line width is set to 0.3 - 0.5 mm, and the delamination position is determined by the delamination information generation algorithm.

[0026] The generation of delamination information in S2 is specifically as follows: S2.1: Obtain the number of plies in the current ply region and find all its adjacent regions; S2.2: Compare the number of plies in region A with that in adjacent region B. If the number of plies in region A is greater than that in region B, perform delamination design.

[0027] The algorithm for finding adjacent regions in S2.1 is specifically as follows: S3.1: The total number of ply regions is N. Starting from the first ply region, denote it as A; S3.2: The initial value of X is 1; S3.3: Find the Xth region in the region list and denote it as B; S3.4: When X ≤ N, compare whether A and B are the same. If A and B are the same, increment the value of X by 1 and re - execute step S3.3; S3.5: If A and B are not the same, find the intersection line of regions A and B; S3.6: If the intersection line exists, Region B is an adjacent region of Region A and is added to the adjacent region list of Region A; S3.7: If the intersection line does not exist, increment the X value by 1 and re - execute step S3.3; S3.8: Increment the X value by 1 and re - execute step S3.3; S3.9: Exit when X > N.

[0028] The layer - loss design algorithm in S2.2 is as follows: S2.2.1: The total number of layers is N, that is, the layer numbers are 1, 2, ……, N; S2.2.2: Take the layer number i, with an initial value of 1; S2.2.3: Determine the size relationship between i and N; S2.2.4: If i ≤ N, obtain the layer with number i in Region A; S2.2.5: If the layer i in Region A exists, obtain the layer with number i in Region B; S2.2.6: If the layer i in Region A does not exist, increment i by 1 and re - execute from step S2.2.3; S2.2.7: If the layer i in Region B exists, increment i by 1 and re - execute from step S2.2.3; S2.2.8: If the layer i in Region B does not exist, find the intersection line between Region A and Region B as the static boundary line; S2.2.9: Input the starting offset o and the layer - loss spacing d; S2.2.10: Offset the static boundary line into Region B, and the offset distance is: , as the layer - loss line; S2.2.11: Increment i by 1 and re - execute from step S2.2.3; S2.2.12: If i > N, the layer - loss information creation of the layer region is completed.

[0029] In S4, by using the HyperMesh mesh processing capabilities and interfaces, the CATIA composite part and layer - loss data are imported into HyperMesh, and the mesh generation, layer property creation, and material coordinate system adjustment are automatically completed to generate a finite - element model. The specific steps are as follows: S4.1: Call the HyperMesh interface to import the finite - element model; S4.2: Select the file output by CATIA for parsing, record the boundary point coordinates and the coordinates within each layer - loss region and store them as dictionary A; S4.3: Loop through the obtained regional information dictionary A. According to the spatial coordinates, match the elements of each region in the finite element model and store them as dictionary B. The dictionary key values are the same as those of dictionary A. S4.4: Analyze the ply information of each region, obtain the actual ply sequence, ply thickness, and ply material information in each ply, and store them as dictionary C. The dictionary key values are the same as those of dictionary A. S4.5: Perform loop processing on dictionary C, obtain the corresponding mesh information of the region from dictionary B through the key value, then create a PCOMP according to the ply parameters in dictionary C, and assign the created PCOMP attributes to the corresponding mesh. S4.6: Readjust the material 0-degree direction of the elements according to the coordinate system of the designed ply. S4.7: Complete the assignment of all region attributes and implement the ply mapping operation.

[0030] As Figures 1-7 shown, this embodiment provides a method for composite material ply missing layer design and finite element modeling. The specific method is as follows: The flowchart intuitively presents the technical execution path: starting from a composite material part, obtaining the number of ply regions, traversing the adjacent regions of each region and comparing the number of plies to determine the "A to B" or "B to A" missing layer direction. After completing the missing layer determination for the entire region, it is connected to the finite element modeling, corresponding to the sub-algorithm logics of steps S1 - S4, adjacent region search, missing layer design, etc. First, read the ply regions of the composite material skin: There are 17 ply regions in this skin, and different regions are represented by different colors according to their ply numbers. Since the number of plies in adjacent regions is not equal, the colors of adjacent regions are different. Secondly, ply missing layer design: After the program reads the ply data of different regions by calling the CATIA software interface, it performs missing layer design. The missing layer information is represented by missing layer lines and visually displayed in the CATIA graphics window. Different missing layer line colors represent different ply angles. Finally, finite element modeling: It can automatically assign the corresponding ply attributes to the meshes of the corresponding regions in HyperMesh according to the ply region information output in CATIA, quickly realizing the creation of missing layer attributes and ply attributes, and greatly improving the finite element modeling efficiency.

[0031] In the description of this specification, the descriptions referring to terms such as "one embodiment", "example", "specific example", etc. mean that the specific features, structures, materials, or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials, or characteristics described can be combined in a suitable manner in any one or more embodiments or examples.

[0032] The preferred embodiments of the present invention disclosed above are only used to help illustrate the present invention. The preferred embodiments do not describe all the details in detail, nor do they limit the invention to the specific embodiments described. Obviously, many modifications and variations can be made according to the content of this specification. These embodiments are selected and specifically described in this specification in order to better explain the principles and practical applications of the present invention, so that those skilled in the art can well understand and utilize the present invention. The present invention is only limited by the claims and their full scope and equivalents.

Claims

1. A method for delamination design and finite element modeling of composite material laminates, characterized in that, It includes the following steps: S1: Obtain the geometric profiles and ply information of all ply areas of the composite part through the CATIA interface and store them as a region list; S2: Utilize the CATIA geometric processing capabilities and interfaces to quickly generate ply missing layer lines on these regional geometries to achieve the display of ply missing layers; S3: Starting from the second ply area, repeat step S2 until the missing layer lines of all ply areas are generated; S4: By utilizing the HyperMesh mesh processing capabilities and interfaces, import the CATIA composite part and missing layer data into HyperMesh, automatically complete mesh generation, ply property creation, and material coordinate system adjustment to generate a finite element model.

2. A composite material ply loss layer design and finite element modeling method according to claim 1, characterized in that The composite part in S1 includes wing skins, fuselage frames in the aerospace field, and lightweight components in the automotive industry.

3. A method for delamination design and finite element modeling of a composite material ply, according to claim 2, characterized in that The ply information stored in S1 includes ply sequence, ply angle, ply thickness, and material type, and is stored in the region list in XML or JSON format.

4. A method for delamination design and finite element modeling of a composite material laminate, according to claim 1, characterized in that, The ply missing layer lines generated in S2 are distinguished by different colors for different ply angles in the CATIA graphics window, the line width is set to 0.3 - 0.5 mm, and the missing layer position is determined through the missing layer information generation algorithm.

5. A design method for missing layers of composite material laminates and a finite element modeling method according to claim 4, characterized in that For the generation of missing layer information in S2, the specific steps are as follows: S2.1: Obtain the number of plies in the current ply area and find all its adjacent areas; S2.2: Compare the number of plies in area A with that in adjacent area B. If the number of plies in area A is greater than that in area B, perform missing layer design.

6. A composite material ply dropout design and finite element modeling method according to claim 5, characterized in that For the algorithm to find adjacent areas in S2.1, the specific steps are as follows: S3.1: The total number of ply areas is N. Starting from the first ply area, denote it as A; S3.2: The initial value of X is 1; S3.3: Find the Xth area in the region list and denote it as B; When X ≤ N, compare whether A and B are the same. If A and B are the same, increment the value of X by 1 and re - execute step S3.3; S3.5: If A and B are not the same, find the intersection line between area A and B; S3.6: If the intersection line exists, then area B is an adjacent area of area A and add it to the adjacent area list of area A; S3.7: If the intersection line does not exist, increment the value of X by 1 and re - execute step S3.3; S3.8: Increment the value of X by 1 and re - execute step S3.3; S3.9: When X > N, exit.

7. A composite material ply loss layer design and finite element modeling method according to claim 5, characterized in that For the missing layer design algorithm in S2.2, the specific steps are as follows: S2.2.1: The total number of plies is N, that is, the ply sequence numbers are 1, 2, ……, N; S2.2.2: Take the ply sequence number i, with an initial value of 1; S2.2.3: Judge the magnitude relationship between i and N; S2.2.4: If i ≤ N, obtain the ply with sequence number i in area A; S2.2.5: If ply i in area A exists, obtain the ply with sequence number i in area B; S2.2.6: If ply i in area A does not exist, then i + 1 and re - execute from step S2.2.3; S2.2.7: If ply i in area B exists, then i + 1 and re - execute from step S2.2.3; S2.2.8: If ply i in region B does not exist, find the intersection line between region A and region B as the static boundary line; S2.2.9: Input the starting offset o and the layer skipping distance d; S2.2.10: The static boundary line is offset into region B by a distance of: , which serves as the layer-loss line; S2.2.11: i + 1, and start executing from step S2.2.3 again; S2.2.12: If i > N, the layer skipping information creation of the ply region is completed.

8. A method for delamination design and finite element modeling of a composite material ply, according to claim 1, characterized in that In S4, by using the HyperMesh mesh processing capabilities and interfaces, the CATIA composite part and the layer skipping data are imported into HyperMesh, and the mesh generation, ply property creation, and material coordinate system adjustment are automatically completed to generate a finite element model. The specific steps are as follows: S4.1: Call the HyperMesh interface to import the finite element model; S4.2: Select the file output by CATIA for parsing, record the boundary point coordinates and the coordinates within each layer skipping region, and store them as dictionary A; S4.3: Loop through the obtained region information dictionary A, match the elements of each region in the finite element model according to the spatial coordinates, and store them as dictionary B. The dictionary Key values are the same as those of dictionary A; S4.4: Parse the ply information of each region, obtain the actual ply sequence, ply thickness, and ply material information in each ply, and store them as dictionary C. The dictionary Key values are the same as those of dictionary A; S4.5: Loop through dictionary C, obtain the corresponding mesh information of the region from dictionary B through the Key value, then create PCOMP according to the ply parameters in dictionary C, and assign the created PCOMP properties to the corresponding meshes; S4.6: Readjust the material 0-degree direction of the elements according to the coordinate system of the designed ply; S4.7: Complete the assignment of all region properties to achieve the ply mapping operation.

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