Modeling method and electronic equipment for honeycomb aluminum partition adhesive coupler

Abstract

This application discloses a modeling method and electronic device for a honeycomb aluminum partition adhesive coupler. The method includes: establishing an equivalent honeycomb aluminum block model, which reflects the geometry, arrangement, and mechanical properties of the honeycomb aluminum; establishing a finite element model of the cotton-fabric adhesive coupler using beam elements; connecting the finite element model of the cotton-fabric adhesive coupler with the honeycomb aluminum block model, and setting the failure criteria and failure parameters of the beam elements; obtaining material mechanical property parameters through multi-level calibration tests of the cotton-fabric adhesive coupler, and iteratively correcting the finite element model based on the material mechanical property parameters to obtain a honeycomb aluminum partition adhesive coupler model for honeycomb aluminum barrier collision simulation. This application can improve the accuracy and computational efficiency of honeycomb aluminum barrier collision simulation.

Description

Technical Field

[0001] This application relates to the field of automotive collision simulation technology, and in particular to a modeling method and electronic device for a honeycomb aluminum partition adhesive coupler. Background Technology

[0002] With the rapid development of the automotive industry, computer-based collision simulation has become an indispensable key tool in automotive safety research and development, effectively controlling development costs, shortening the R&D cycle, and improving design quality. Honeycomb aluminum materials, due to their high strength, low density, and excellent energy absorption characteristics, are widely used in the manufacture of deformable energy-absorbing barriers required by collision regulations. The cotton-adhesive coupler, as the core component connecting different honeycomb aluminum blocks, directly determines the reliability of the entire barrier model through the accuracy of its mechanical behavior simulation. However, current technologies typically use shell elements to simulate the cotton-adhesive coupler. This method not only fails to accurately reflect its anisotropic mechanical characteristics—prone to brittle fracture in the normal direction and possessing high resistance to deformation in the tangential direction—but also suffers from large mesh sizes, long computation times, and high resource consumption. Consequently, it is difficult to balance accuracy and computational efficiency in honeycomb aluminum barrier collision simulation, failing to meet the actual needs of automotive safety research and development.

[0003] Therefore, improving the accuracy and computational efficiency of honeycomb aluminum barrier collision simulation, and providing a reliable and efficient analysis tool for the rapid design and performance optimization of automotive safety components, has become an urgent technical problem to be solved. Summary of the Invention

[0004] The embodiments of this application provide a modeling method and electronic device for honeycomb aluminum partition adhesive couplers, which can at least to some extent improve the accuracy and computational efficiency of honeycomb aluminum barrier collision simulation.

[0005] Other features and advantages of this application will become apparent from the following detailed description, or may be learned in part from practice of this application.

[0006] According to a first aspect of the embodiments of this application, a modeling method for a honeycomb aluminum partition adhesive coupler is provided. The method includes: establishing an equivalent honeycomb aluminum block model, the honeycomb aluminum block model being used to reflect the geometry, arrangement, and mechanical properties of the honeycomb aluminum; establishing a finite element model of the cotton-fabric adhesive coupler using beam elements; connecting the finite element model of the cotton-fabric adhesive coupler with the honeycomb aluminum block model, and setting the failure criteria and failure parameters of the beam elements; obtaining material mechanical property parameters through multi-level calibration tests of the cotton-fabric adhesive coupler, and iteratively correcting the finite element model based on the material mechanical property parameters to obtain a honeycomb aluminum partition adhesive coupler model applicable to honeycomb aluminum barrier collision simulation.

[0007] In some embodiments of this application, based on the aforementioned scheme, the establishment of an equivalent honeycomb aluminum block model includes: selecting the origin of the coordinate system as the modeling reference, and establishing three two-dimensional shell units representing one side of the honeycomb hole; generating a complete regular hexagonal honeycomb hole unit by rotating and copying it around the center point; arraying and copying the regular hexagonal honeycomb hole unit along the length, width, and height directions of the honeycomb aluminum block entity to construct a single honeycomb aluminum block; copying the single honeycomb aluminum block to obtain two honeycomb aluminum blocks, and connecting the two honeycomb aluminum blocks together through the cotton adhesive coupling body.

[0008] In some embodiments of this application, based on the aforementioned scheme, the step of establishing a finite element model of the cotton-adhesive coupling body using beam elements includes: arranging a layer of beam elements in the original partition plane, wherein the cross-sectional shape of the beam elements is consistent with the cross-sectional geometry of the honeycomb aluminum on both sides, and the node positions of the beam elements correspond one-to-one with the node coordinates on the corresponding cross-section of the honeycomb aluminum blocks; extending from the beam element nodes in the original partition plane to both sides to establish a beam element structure for connecting the honeycomb aluminum blocks.

[0009] In some embodiments of this application, based on the foregoing scheme, connecting the finite element model of the cotton adhesive coupler with the honeycomb aluminum block model includes: connecting the beam units extending on both sides to the beam unit nodes in the original partition plane and the corresponding nodes of the honeycomb aluminum block through a common node method.

[0010] In some embodiments of this application, based on the aforementioned scheme, the acquisition of material mechanical property parameters through multi-level calibration tests of the cotton-viscose coupler includes: conducting static calibration tests of the cotton-viscose coupler to obtain the basic elasticity, plasticity, and failure parameters of the material; conducting dynamic calibration tests of the cotton-viscose coupler to obtain the mechanical response and failure behavior parameters of the material under high strain rates; and conducting calibration tests of the combined structure to obtain the failure mode and failure parameters of the combined structure.

[0011] In some embodiments of this application, based on the aforementioned scheme, the static calibration test of the cotton-viscose coupler to obtain the basic elasticity, plasticity, and failure parameters of the material includes: preparing a sample of the cotton-viscose coupler to be tested; conducting a quasi-static uniaxial tensile test on the sample to be tested to obtain the yield stress, elastic modulus, and failure strain; and conducting a torsion test on the sample to be tested to obtain the torsional stiffness and shear modulus.

[0012] In some embodiments of this application, based on the aforementioned scheme, the dynamic calibration test of the cotton-viscose coupler to obtain the mechanical response and failure behavior parameters of the material under high strain rate includes: preparing a square cotton-viscose coupler test sample; constraining the degree of freedom of the test sample in the plane normal direction; dynamically impacting the central region of the test sample with a square impactor at different rates; recording the impact force displacement velocity history and failure process to obtain the failure mode and energy absorption characteristics of the coupler under high strain rate.

[0013] In some embodiments of this application, based on the aforementioned scheme, the step of conducting a combined structure calibration test to obtain the failure mode and failure parameters of the combined structure includes: preparing an I-shaped simplified connection unit composed of two small honeycomb aluminum blocks and an intermediate cotton adhesive coupling body; conducting a tangential shear test on the I-shaped simplified connection unit to measure its load-displacement curve deformation failure process and final failure mode; and conducting a normal peel test on the I-shaped simplified connection unit to measure its load-displacement curve deformation failure process and final failure mode.

[0014] In some embodiments of this application, based on the aforementioned scheme, the iterative correction of the finite element model based on the material mechanical property parameters includes: establishing a simulation model corresponding to each level of calibration test; substituting the material mechanical property parameters obtained from each level of calibration test into the simulation model to calibrate the corresponding parameters of the beam element; and updating the failure parameters of the beam element so that the deformation process and failure mode of the coupled body in the simulation are consistent with the experimental observation results.

[0015] According to a second aspect of the embodiments of this application, an electronic device is provided, the electronic device including one or more processors and one or more memories, the one or more memories storing at least one computer program instruction, the at least one computer program instruction being loaded and executed by the one or more processors to perform the operation as described in any of the first aspects above.

[0016] Based on the technical solution proposed in this application, by establishing an equivalent honeycomb aluminum block model that accurately reflects the geometry and arrangement of honeycomb aluminum, a precise geometric basis can be provided for honeycomb aluminum barrier collision simulation. This avoids the problem of insufficient simulation accuracy caused by geometric model deviations, ensuring that the simulation model can realistically reproduce the actual structural characteristics of honeycomb aluminum. Using beam elements to establish the finite element model of the cotton-adhesive coupler can accurately simulate the anisotropic mechanical behavior and actual failure modes of the cotton-adhesive coupler. Compared with the shell elements commonly used in existing technologies, the mechanical constitutive model of beam elements is simpler, effectively reducing mesh size and computational resource consumption, thereby significantly improving the computational efficiency of honeycomb aluminum barrier collision simulation and shortening the simulation cycle. Connecting the finite element model of the cotton-adhesive coupler with the honeycomb aluminum block model and reasonably setting the failure criteria and failure parameters of the beam elements can ensure the accurate transmission of force and deformation between the models, making the mechanical response of the cotton-adhesive coupler more consistent with reality and further improving simulation accuracy. By obtaining material mechanical property parameters through multi-level calibration tests of the cotton-viscose coupler and iteratively correcting the finite element model based on these parameters, the material properties, deformation process, and failure mode of the cotton-viscose coupler in the simulation model can be made consistent with the actual experimental results. This significantly improves the overall accuracy of the honeycomb aluminum barrier collision simulation and ensures high reliability of the simulation results. In summary, the technical solution of this application can improve computational efficiency while ensuring simulation accuracy, thereby providing a reliable and efficient analysis tool for the rapid design and performance optimization of automotive safety components. This helps R&D personnel reduce their reliance on physical prototypes and repeated tests, shorten the R&D cycle, and control R&D costs. Attached Figure Description

[0017] The accompanying drawings, which are incorporated in and form part of this specification, illustrate embodiments consistent with this application and, together with the description, serve to explain the principles of this application. It is obvious that the drawings described below are merely some embodiments of this application, and those skilled in the art can obtain other drawings based on these drawings without any inventive effort. In the drawings: Figure 1 A flowchart illustrating the modeling method of the honeycomb aluminum partition adhesive coupler in an embodiment of this application is shown; Figure 2 A schematic diagram of a honeycomb hole model from an embodiment of this application is shown; Figure 3 A schematic diagram of a honeycomb aluminum block model from an embodiment of this application is shown; Figure 4 A schematic diagram of the connection between the beam element and the honeycomb hole in an embodiment of this application is shown; Figure 5 A schematic diagram of the static calibration test specimen of the coupler in an embodiment of this application is shown; Figure 6 A schematic diagram of the quasi-static uniaxial tensile test plane is shown in an embodiment of this application; Figure 7 A schematic diagram of the torsion test plane in an embodiment of this application is shown; Figure 8 A schematic diagram of the dynamic calibration test specimen of the coupler in an embodiment of this application is shown; Figure 9 A schematic diagram of the dynamic calibration test plane of the square impact head in an embodiment of this application is shown; Figure 10 A schematic diagram of the combined structure in an embodiment of this application is shown; Figure 11 A schematic diagram of a tangential shear test in an embodiment of this application is shown; Figure 12 A schematic diagram of a normal tensile peel test in an embodiment of this application is shown; Figure 13 A schematic diagram of the structure of an electronic device according to an embodiment of this application is shown. Detailed Implementation

[0018] 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, and 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.

[0019] Furthermore, the described features, structures, or characteristics can be combined in any suitable manner in one or more embodiments. Numerous specific details are provided in the following description to give a thorough understanding of embodiments of this application. However, those skilled in the art will recognize that the technical solutions of this application can be practiced without one or more of the specific details, or other methods, components, apparatuses, steps, etc., can be employed. In other instances, well-known methods, apparatuses, implementations, or operations are not shown or described in detail to avoid obscuring various aspects of this application.

[0020] The block diagrams shown in the accompanying drawings are merely functional entities and do not necessarily correspond to physically independent entities. That is, these functional entities can be implemented in software, in one or more hardware modules or integrated circuits, or in different network and / or processor devices and / or microcontroller devices. It should also be noted that, for the sake of simplicity, certain components in the drawings that do not affect the interpretation of the technical solution of this application have been appropriately omitted.

[0021] The flowchart shown in the attached diagram is for illustrative purposes only and does not necessarily include all content and operations / steps, nor does it necessarily have to be performed in the described order. For example, some operations / steps can be broken down, while others can be combined or partially combined. Therefore, the actual execution order may change depending on the actual situation.

[0022] In the description of this application, it should be understood that the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Therefore, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this application, unless otherwise stated, "multiple" means two or more.

[0023] In automotive R&D, computer-based simulation has become an indispensable key research method and engineering verification tool in order to effectively control development costs, shorten the R&D cycle, and improve design quality. The accuracy of automotive crash simulation depends not only on the sophistication of the finite element method (FEM) core algorithm but also fundamentally on the accuracy of the model itself. Therefore, constructing a barrier simulation model that accurately reflects the mechanical properties of honeycomb aluminum materials is a crucial prerequisite for ensuring the validity of crash analysis results.

[0024] Honeycomb aluminum is characterized by high strength and low density, and due to its structural features, it possesses strong energy absorption properties. In the field of automotive safety research and development, honeycomb aluminum can be used to manufacture deformable energy-absorbing barriers required by collision regulations.

[0025] Honeycomb aluminum is mostly composed of honeycomb aluminum blocks and partitions that serve as connectors. In some full-width deformable fixed barriers, partitions are replaced by cotton cloth and adhesive, where the adhesive plays the main role in bonding two honeycomb aluminum blocks with different thicknesses and pore sizes, and the cotton cloth acts as a carrier for the adhesive. When bonding two honeycomb aluminum blocks, one block is usually placed horizontally on the work surface. Then, the cotton cloth is cut to match the cross-sectional dimensions of the honeycomb aluminum block, and adhesive is evenly applied to its surface. Next, the other honeycomb aluminum block is aligned and pressed onto the adhesive-coated cotton cloth, and a tight connection is formed after natural curing. During this process, the thickness of the cured adhesive must be controlled to 2mm, and the cotton cloth must be centered in the adhesive layer in the thickness direction.

[0026] In existing simulation modeling practices, the deformation and failure of partitions are usually simulated using shell elements. However, the inventors of this application have found that this modeling method has obvious limitations: on the one hand, shell elements are difficult to accurately reflect the anisotropic characteristics of the cotton-viscose coupler in mechanical response—that is, it is prone to brittle fracture along the normal direction of the partition (i.e., the main impact direction of the test vehicle), but exhibits high resistance to deformation along the plane direction of the partition (i.e., the tangential direction); on the other hand, shell element models usually have large mesh sizes, long computation time, and require a lot of computing resources.

[0027] In this context, this application proposes a modeling scheme for honeycomb aluminum barrier adhesive couplers. The aim is to overcome the shortcomings of existing shell element simulations of cotton adhesive couplers, which suffer from low accuracy and poor efficiency. This scheme accurately simulates the anisotropic mechanical behavior and actual failure modes of cotton adhesive couplers. While maintaining computational efficiency, it significantly improves the accuracy and computational efficiency of honeycomb aluminum barrier collision simulation, thereby providing a reliable and efficient analysis tool for the rapid design and performance optimization of automotive safety components.

[0028] Specifically, the cotton-viscose coupler exhibits significant anisotropic characteristics in its mechanical response. It is prone to brittle fracture along the normal direction of the partition (the main impact direction of the test vehicle), while showing high resistance to deformation along the tangential direction of the partition plane. Furthermore, its failure initiation location, propagation path, and final morphology under different loads exhibit clear physical laws. However, existing technologies commonly use shell element models to simulate the cotton-viscose coupler. This method not only struggles to accurately reproduce the aforementioned anisotropic mechanical properties and fails to realistically recreate the failure process and damage morphology of the coupler during collision, leading to significant discrepancies between simulation results and physical experiments, but also suffers from problems such as large mesh size, long computation time, and high hardware resource consumption. This makes it difficult to balance accuracy and computational efficiency in honeycomb aluminum barrier collision simulation, failing to meet the actual needs of rapid iteration in automotive safety research and development.

[0029] Next, this application will elaborate on the modeling scheme of the proposed honeycomb aluminum partition adhesive coupler. (Refer to...) Figure 1 The flowchart illustrates a modeling method for a honeycomb aluminum partition adhesive coupler according to an embodiment of this application. This method can be executed by a device with computational processing capabilities, such as... Figure 1 As shown, the method includes at least steps 110 to 140, which are described in detail below: In step 110, an equivalent honeycomb aluminum block model is established, which is used to reflect the geometric shape, arrangement and mechanical properties of honeycomb aluminum.

[0030] In this application, the honeycomb aluminum block model is constructed using an equivalent modeling approach. While maintaining the basic geometric shape of the regular hexagonal honeycomb holes, the mesh size and computational efficiency can be controlled and improved by increasing the diameter and side length of the honeycomb holes in the simulation. Simultaneously, by specifically adjusting the wall thickness parameters of the honeycomb holes, the model can be made equivalent to the actual honeycomb aluminum in terms of overall mechanical properties. This accurately reflects its crushing deformation law, load-bearing strength, and energy absorption characteristics under collision loads, providing a reliable structural and mechanical benchmark for subsequent connection modeling of the cotton-adhesive coupler and overall honeycomb aluminum barrier collision simulation.

[0031] In this application, the establishment of an equivalent honeycomb aluminum block model can be performed according to the following steps 111 to 114: Step 111: Select the origin of the coordinate system as the modeling reference and establish three two-dimensional shell elements representing one side of the honeycomb hole.

[0032] Step 112: Generate a complete regular hexagonal honeycomb cell by rotating around the center point.

[0033] Step 113: The regular hexagonal honeycomb cell unit is arrayed and replicated along the length, width and height of the honeycomb aluminum block to construct a single honeycomb aluminum block.

[0034] Step 114: Copy the single honeycomb aluminum block to obtain two honeycomb aluminum blocks, which are connected by the cotton adhesive coupling body.

[0035] In this application, a suitable coordinate system origin can be selected as the modeling reference. This origin can be set at the lower left vertex of the honeycomb aluminum block to facilitate subsequent array replication operations. Three two-dimensional shell elements representing a single side of the honeycomb hole are established. The length of these three shell elements can be determined according to the actual side length of the honeycomb hole.

[0036] For example, refer to Figure 2 The diagram shows a schematic of a honeycomb hole model in an embodiment of this application, such as... Figure 2 As shown, the diameter of the honeycomb hole is 31.75 mm, and the length of a single side is 18.33 mm. When the side length of the honeycomb hole is 18.33 mm, it can be divided into three shell elements with lengths of 4.67 mm, 8.99 mm, and 4.67 mm respectively. The element length can be set to 5 mm. This division method can control the number of meshes while ensuring simulation accuracy and avoid excessive computation.

[0037] In this application, a complete regular hexagonal honeycomb cell unit can be generated by rotating and replicating around a center point. A regular hexagon has six equal sides and six equal interior angles. The rotation angle can be set to 60 degrees, and a complete honeycomb cell unit can be obtained by rotating five times in sequence.

[0038] In this application, the regular hexagonal honeycomb cell units can be arrayed and replicated along the length, width, and height of the honeycomb aluminum block to construct a single honeycomb aluminum block. The overall structure of the single honeycomb aluminum block formed by arraying and replicating multiple regular hexagonal honeycomb cell units along the length, width, and height directions clearly presents the regular arrangement of the honeycomb cells inside the honeycomb aluminum block and the external contour shape of the single honeycomb aluminum block.

[0039] The number of array replicas can be calculated based on the actual size of the aluminum honeycomb blocks. For example, refer to... Figure 3 The diagram shows a schematic of a honeycomb aluminum block model in an embodiment of this application, as shown below. Figure 3 As shown, when the overall dimensions of the honeycomb aluminum barrier are 2000 mm in length, 300 mm in width, and 1000 mm in height, and it is composed of two honeycomb aluminum blocks with dimensions of 2000 mm in length, 150 mm in width, and 1000 mm in height, the number of honeycomb holes in a single honeycomb aluminum block in the length direction can be approximately 63 (2000 mm divided by 31.75 mm), the number of honeycomb holes in the height direction can be 36, and the number of honeycomb holes in the width direction can be 30 (150 mm divided by 5 mm).

[0040] In this application, the honeycomb aluminum block model established through the above steps can accurately reflect the actual geometry, arrangement, and mechanical properties of the honeycomb aluminum, providing a reliable foundation for subsequent coupled body modeling. This model can realistically simulate the energy absorption characteristics of the honeycomb aluminum material, ensuring the simulation accuracy of the entire barrier model.

[0041] In this application, the single honeycomb aluminum block can be replicated to obtain two honeycomb aluminum blocks, which are connected by the cotton adhesive coupling body. The spacing between the two honeycomb aluminum blocks can be set to 2 mm, which is consistent with the actual thickness of the cured cotton adhesive coupling body to ensure the geometric accuracy of the model.

[0042] Continue to refer to Figure 1 In step 120, a finite element model of the cotton-viscose coupling body is established using beam elements.

[0043] In this application, beam elements can be used to establish the finite element model of the cotton-viscose coupler. The beam element is a one-dimensional finite element that can simulate the mechanical behavior of rods such as tension, compression, bending, and shear. Its mechanical constitutive model is simple, its computational efficiency is high, and it can flexibly set various failure modes such as axial, shear, and bending. It is very suitable for simulating materials with obvious anisotropic characteristics, such as cotton-viscose couplers.

[0044] In this application, the establishment of the finite element model of the cotton-viscose coupling body using beam elements can be performed according to the following steps 121 to 122: Step 121: Arrange a layer of beam units in the original partition plane. The cross-sectional shape of the beam units is consistent with the cross-sectional geometry of the honeycomb aluminum on both sides, and the node positions of the beam units correspond one-to-one with the node coordinates on the corresponding cross-section of the honeycomb aluminum blocks.

[0045] Step 121: Extend the beam unit nodes in the original partition plane to both sides to establish a beam unit structure for connecting the honeycomb aluminum blocks.

[0046] In this application, the element length of the beam element can be set to 18.33 mm, which is consistent with the side length of the honeycomb hole. This ensures that the nodes of the beam element and the nodes of the honeycomb aluminum block can be accurately aligned, facilitating subsequent connection operations.

[0047] Reference Figure 4 The diagram shows the connection between the beam unit and the honeycomb holes in the embodiment of this application. It shows the connection relationship between the beam unit structure of the cotton adhesive coupling body and the honeycomb holes on both sides. The beam unit located in the original partition plane is labeled as inter, and the beam units extending from the inter beam unit node to both sides are labeled as side1 and side2, respectively. The diagram also shows the common node connection method between each beam unit node and the corresponding node of the honeycomb hole.

[0048] like Figure 4 As shown, the in-plane beam element can be named the inter beam, mainly used to simulate the mechanical behavior of the cotton-adhesive coupler in the plane. Extending from the beam element nodes in the original partition plane to both sides, the extension length can be set to 5 mm. The beam elements extending on both sides can be named side1 beam and side2 beam, respectively. These extended beam elements are mainly used to connect the inter beam to the honeycomb aluminum blocks on both sides, ensuring that forces can be accurately transmitted between the coupler and the honeycomb aluminum blocks.

[0049] By employing beam elements to establish a finite element model of the cotton-viscose coupling, the problem of traditional shell element models failing to accurately reflect the anisotropic mechanical characteristics of the material can be effectively solved. Beam elements allow for the setting of mechanical parameters in different directions, such as axial, shear, and bending, thus realistically simulating the characteristics of the cotton-viscose coupling, which is prone to brittle fracture in the normal direction and exhibits high resistance to deformation in the tangential direction. Furthermore, the beam element mesh is significantly smaller than that of the shell element, significantly reducing computational load and improving simulation efficiency.

[0050] Continue to refer to Figure 1 In step 130, the finite element model of the cotton adhesive coupler is connected to the honeycomb aluminum block model, and the failure criteria and failure parameters of the beam element are set.

[0051] In this application, the connection between the finite element model of the cotton adhesive coupler and the honeycomb aluminum block model can be performed according to the following step 131: Step 131: By using a common node method, the beam units extending on both sides are connected to the beam unit nodes and the corresponding nodes of the honeycomb aluminum blocks in the original partition plane, respectively.

[0052] In this application, during the connection process, the beam elements extending on both sides can be connected to the beam element nodes and corresponding nodes of the honeycomb aluminum blocks within the original partition plane using a common node method. Common node connection refers to merging the nodes of two elements into one node, giving them the same displacement and degrees of freedom. This connection method ensures direct connection between elements, maintains displacement coordination and strain continuity at the interface, thereby establishing a stable force transmission path and guaranteeing the realism and reliability of load and deformation transmission in the simulation.

[0053] Failure criteria and parameters for beam elements are established to simulate the failure behavior of cotton-viscose couplers under actual loads. Failure criteria can include various modes such as axial tensile failure, shear failure, and bending failure. For example, the beam element can be set to fracture when its axial stress reaches a preset failure stress, and to undergo shear failure when its shear stress reaches a preset shear failure stress. Initial values ​​for the failure parameters can be set based on experience or relevant literature, and will be subsequently corrected through calibration tests.

[0054] By using a common-node connection method, accurate force transmission between the cotton-adhesive coupler and the honeycomb aluminum block can be ensured, avoiding connection failures or abnormal force transmission. By setting reasonable failure criteria and parameters, the beam element can exhibit failure behavior similar to that of actual materials during simulation, further enhancing the realism of the simulation model.

[0055] Continue to refer to Figure 1 In step 140, the material mechanical property parameters are obtained through multi-level calibration tests of the cotton adhesive coupler, and the finite element model is iteratively corrected based on the material mechanical property parameters to obtain the honeycomb aluminum partition adhesive coupler model applied to the collision simulation of the honeycomb aluminum barrier.

[0056] In this application, failure criteria and parameters of beam elements can be set according to the mechanical properties of materials to simulate the failure behavior of cotton-viscose couplers under actual loads. The material parameters and failure modes of the beam elements can be calibrated experimentally. The quasi-static and dynamic stress-strain curves, elastic modulus, yield strength, and failure strain of the coupler in different directions (tangential and normal) are measured. The failure initiation location, propagation path, and final morphology under tensile, shear, and impact loads are observed and recorded. The strength of the bonding interface between the coupler and the honeycomb aluminum is evaluated to ensure the reliability of the connection model in the simulation.

[0057] In this application, multi-level calibration tests may include static calibration tests, dynamic calibration tests, and combined structure calibration tests, which can comprehensively obtain the mechanical property parameters of materials from different dimensions and provide reliable data support for the parameter calibration of simulation models.

[0058] In this application, the acquisition of material mechanical property parameters through multi-stage calibration tests of the cotton-viscose coupler can be performed according to the following steps 141 to 143: Step 141: Conduct a static calibration test on the cotton-viscose coupler to obtain the basic elasticity, plasticity, and failure parameters of the material.

[0059] Step 142: Conduct dynamic calibration tests on the cotton-viscose coupler to obtain the mechanical response and failure behavior parameters of the material under high strain rates.

[0060] Step 143: Conduct a calibration test on the combined structure to obtain the failure modes and failure parameters of the combined structure.

[0061] In this application, the static calibration test of the cotton-viscose coupler to obtain the basic elasticity, plasticity, and failure parameters of the material can be performed according to the following steps 1411 to 1413: Step 1411: Prepare the cotton-viscose coupler sample to be tested.

[0062] Step 1412: Perform a quasi-static uniaxial tensile test on the test specimen to obtain the yield stress, elastic modulus and failure strain.

[0063] Step 1413: Perform a torsion test on the sample to be tested to obtain the torsional stiffness and shear modulus.

[0064] Reference Figures 5 to 7 The diagrams show schematic diagrams of the static calibration test specimen, the quasi-static uniaxial tensile test plane, and the torsion test plane in the embodiments of this application.

[0065] In this application, as Figures 5 to 7As shown, a cotton-viscose coupler sample was prepared. The sample dimensions were 150 mm × 15 mm × 2 mm, which corresponds to the actual thickness of the coupler and ensures the representativeness of the test results. A quasi-static uniaxial tensile test was performed on the sample. The sample was clamped at both ends with clamping lengths of 30 mm each, and stretched at a constant strain rate of 1 mm / min until failure. The force-displacement curve was recorded to obtain basic mechanical parameters such as yield stress, elastic modulus, and failure strain. A torsion test was then performed on the sample. Similarly, the sample was clamped at both ends with clamping, and a constant torque of 2 Nm was applied. The corresponding torsional deformation was measured, and the shear modulus and torsional stiffness were calculated. Based on the test results, a corresponding finite element simulation model was established. The measured material parameters were used to calibrate and correct the equivalent stiffness and failure criteria of the beam elements in the model to improve the reliability of the simulation model.

[0066] In this application, the dynamic calibration test of the cotton-viscose coupler to obtain the mechanical response and failure behavior parameters of the material under high strain rate can be performed according to the following steps 1421 to 1424: Step 1421: Prepare a square cotton-viscose coupler sample to be tested.

[0067] Step 1422: Constrain the degree of freedom of the sample under test in the plane normal direction.

[0068] Step 1423: Dynamically impact the central region of the sample under test with a square impactor at different rates.

[0069] Step 1424: Record the impact force displacement velocity history and failure process to obtain the failure mode and energy absorption characteristics of the coupling body under high strain rate.

[0070] Reference Figures 8 to 9 The diagrams show schematic diagrams of the dynamic calibration test specimen of the coupler in the embodiments of this application, and a schematic diagram of the dynamic calibration test plane of the square impact head.

[0071] In this application, as Figures 8 to 9As shown, a square cotton-viscose coupler sample was prepared, with dimensions of 300 mm × 300 mm × 2 mm. The degree of freedom of the sample in the normal direction of the plane was constrained, with a constraint length of 25 mm, to simulate the boundary conditions of the coupler in an actual collision. A square impactor was used to dynamically impact the central region of the sample at different rates: 10 km / h, 20 km / h, and 30 km / h. The impact force, displacement, velocity history, and failure process were recorded to obtain the failure mode and energy absorption characteristics of the coupler under high strain rates. Based on the experimental results, a corresponding finite element simulation model was established, and the dynamic constitutive parameters and failure criteria of the beam elements in the normal direction were calibrated and corrected to improve the model's prediction accuracy in the transient response of the collision.

[0072] In this application, the calibration test of the composite structure to obtain the failure mode and failure parameters of the composite structure can be performed according to the following steps 1431 to 1433: Step 1431: Prepare an I-shaped simplified connection unit consisting of two small honeycomb aluminum blocks and a cotton adhesive coupler in the middle.

[0073] Step 1432: Perform a tangential shear test on the I-shaped simplified connection unit to measure its load-displacement curve deformation failure process and final failure mode.

[0074] Step 1433: Perform a normal peel test on the I-shaped simplified connection unit to measure its load-displacement curve deformation failure process and final failure mode.

[0075] Reference Figures 10 to 12 The diagrams show the combined structure, tangential shear test, and normal tensile peel test of the embodiments of this application.

[0076] In this application, as Figures 10 to 12 As shown, a simplified I-shaped connection unit was prepared, consisting of two small honeycomb aluminum blocks and an intermediate cotton adhesive coupling body. The dimensions of the small honeycomb aluminum blocks can be 200 mm × 100 mm × 30 mm, and the dimensions of the intermediate coupling body are consistent with the connection surface dimensions of the honeycomb aluminum blocks. A tangential shear test was performed on the simplified I-shaped connection unit, applying a total in-plane reverse force of 5 kN to the two honeycomb aluminum blocks, subjecting the intermediate coupling body layer to pure shear. Its load-displacement curve, deformation failure process, and final failure mode were measured. A normal peel test was also performed on the simplified I-shaped connection unit, applying a total reverse normal force of 10 kN to the two honeycomb aluminum blocks, subjecting the connection layer to tensile peel. Its load-displacement curve, deformation failure process, and final failure mode were measured.

[0077] In this application, the results obtained can be directly used to correct key parameters such as equivalent shear stiffness, axial stiffness, and failure force threshold in the beam element model, thereby accurately calibrating the model and ensuring that its mechanical response is consistent with physical experiments.

[0078] In this application, static calibration tests can be used to obtain the basic mechanical parameters of the cotton-viscose coupler under quasi-static loads, providing a basis for setting the elastic and plastic properties of the beam elements. Dynamic calibration tests can be used to obtain the mechanical response and failure behavior of the material under high strain rates, ensuring the accuracy of the simulation model under high-speed impact conditions such as automobile collisions. Combined structure calibration tests can directly verify the effectiveness of the beam element connection model, ensuring that the mechanical response of the entire connection structure is consistent with the actual situation. The combination of multi-level calibration tests can comprehensively and accurately obtain the mechanical performance parameters of the material, providing a strong guarantee for the high precision of the simulation model.

[0079] In this application, the iterative correction of the finite element model based on the material mechanical property parameters can be performed according to the following steps 144 to 146: Step 144: Establish simulation models corresponding to each level of calibration test.

[0080] Step 145: Substitute the material mechanical property parameters obtained from each level of calibration test into the simulation model to calibrate the corresponding parameters of the beam element.

[0081] Step 146: Update the failure parameters of the beam element to make the deformation process and failure mode of the coupled body in the simulation consistent with the experimental observation results.

[0082] In this application, the geometric dimensions, boundary conditions, loading methods, etc., of the simulation model should be consistent with those of the actual experiment. Material mechanical property parameters obtained from various calibration tests are substituted into the simulation model to calibrate the corresponding parameters of the beam elements. For example, the elastic modulus, yield strength, and failure strain obtained from static tensile tests are substituted into the simulation model to adjust the axial mechanical parameters of the beam elements; the shear modulus and torsional stiffness obtained from torsion tests are substituted into the simulation model to adjust the shear mechanical parameters of the beam elements; the dynamic failure parameters obtained from dynamic impact tests are substituted into the simulation model to adjust the dynamic constitutive relationship of the beam elements; the load-displacement curves obtained from combined structure tests are compared with the simulation results to adjust parameters such as the failure threshold of the beam elements.

[0083] In this application, the failure parameters of the beam elements are updated to ensure that the deformation process and failure mode of the coupled body in the simulation are consistent with the experimental observation results. If there is a deviation between the simulation results and the experimental results, the parameters of the beam elements need to be adjusted, and the simulation calculation needs to be repeated until the error between the simulation results and the experimental results is within the allowable range. Through multiple iterative corrections, the parameters of the simulation model can be continuously optimized, enabling the model to accurately simulate the actual mechanical behavior of the cotton-viscose coupled body.

[0084] In this application, by establishing a simulation model corresponding to the experiment and calibrating the parameters, the material properties of the beam elements can be ensured to be highly consistent with the actual materials. Through iterative correction, the gap between the simulation results and the experimental results can be continuously narrowed, enabling the simulation model to accurately predict the deformation and failure behavior of the cotton-adhesive coupler under various loads. The final honeycomb aluminum partition adhesive coupler model can work in conjunction with the honeycomb aluminum block model to form a high-precision honeycomb aluminum barrier simulation model, providing a reliable tool for automotive collision safety analysis.

[0085] Based on the technical solution proposed in this application, by using beam elements instead of traditional shell elements to simulate the cotton-viscose coupler, the problem of shell elements' inability to accurately reflect the anisotropic mechanical characteristics of the material can be effectively solved. Simultaneously, the mechanical constitutive model of beam elements is simpler, significantly reducing mesh size and computational resource consumption, thereby improving simulation efficiency. By setting up multi-level calibration tests, the mechanical performance parameters of the cotton-viscose coupler can be comprehensively obtained from three dimensions: static, dynamic, and combined structure. This ensures that the material properties of the beam elements in the simulation model are highly consistent with the actual material, thus making the deformation process and failure mode of the coupler in the simulation more consistent with the actual experimental results, effectively improving the overall accuracy of the honeycomb aluminum barrier collision simulation. Connecting the beam elements and the honeycomb aluminum block model through shared nodes ensures accurate force and deformation transmission, further enhancing the reliability of the simulation model. The technical solution of this application can significantly improve the confidence level of collision simulation predictions while ensuring computational efficiency, reducing reliance on physical prototypes and repeated tests during the R&D process, and providing a reliable and efficient analysis tool for the rapid design and performance optimization of automotive safety components.

[0086] Based on the same inventive concept, this application also provides an electronic device, see reference. Figure 13 The diagram shows a schematic of the structure of an electronic device in an embodiment of this application. The electronic device includes one or more memories 1304, one or more processors 1302, and at least one computer program (computer program instruction) stored in the memory 1304 and executable on the processor 1302. When the processor 1302 executes the computer program, it implements the modeling method of the honeycomb aluminum partition adhesive coupler as described above.

[0087] Among them, Figure 13 In this document, a bus architecture (represented by bus 1300) is used. Bus 1300 may include any number of interconnected buses and bridges, linking various circuits including one or more processors represented by processor 1302 and memory represented by memory 1304. Bus 1300 may also link various other circuits such as peripheral devices, voltage regulators, and power management circuits, which are well known in the art and therefore will not be described further herein. Bus interface 1305 provides an interface between bus 1300 and receiver 1301 and transmitter 1303. Receiver 1301 and transmitter 1303 may be the same element, i.e., a transceiver, providing a unit for communicating with various other devices over a transmission medium. Processor 1302 is responsible for managing bus 1300 and general processing, while memory 1304 may be used to store data used by processor 1302 during operation.

[0088] The functions described herein can be implemented in hardware, software executed by a processor, firmware, or any combination thereof. When implemented in software executed by a processor, the functions can be stored as one or more instructions or codes on or transmitted via a computer-readable medium. Other examples and embodiments are within the scope and spirit of this application and the appended claims. For example, due to the nature of software, the functions described above can be implemented using software executed by a processor, hardware, firmware, hardwired, or any combination thereof. Furthermore, the functional units can be integrated into a single processing unit, or each unit can exist physically separately, or two or more units can be integrated into a single unit.

[0089] In the several embodiments provided in this application, it should be understood that the disclosed technical content can be implemented in other ways. The device embodiments described above are merely illustrative; for example, the division of units can be a logical functional division, and in actual implementation, there may be other division methods. For instance, multiple units or components may be combined or integrated into another system, or some features may be ignored or not executed. Furthermore, the displayed or discussed mutual coupling, direct coupling, or communication connection may be through some interfaces; the indirect coupling or communication connection between units or modules may be electrical or other forms.

[0090] The units described as separate components may or may not be physically separate. Similarly, the components of the control device may or may not be physical units; they may be located in one place or distributed across multiple units. Some or all of the units can be selected to achieve the purpose of this embodiment, depending on actual needs.

[0091] When the integrated unit is implemented as a software functional unit and sold or used as an independent product, it can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of this application, in essence, or the part that contributes to the prior art, or all or part of the technical solution, can be embodied in the form of a software product. This computer software product is stored in a storage medium and includes several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute all or part of the steps of the methods described in the various embodiments of this application. The aforementioned storage medium includes various media capable of storing computer program instructions, such as USB flash drives, read-only memory (ROM), random access memory (RAM), portable hard drives, magnetic disks, or optical disks.

[0092] The above description is merely an embodiment of this application and is not intended to limit this application. Various modifications and variations can be made to this application by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this application should be included within the scope of the claims of this application.

Claims

1. A modeling method for a honeycomb aluminum partition adhesive coupler, characterized in that, The method includes: An equivalent honeycomb aluminum block model is established, which is used to reflect the geometric shape, arrangement and mechanical properties of honeycomb aluminum; A finite element model of the cotton-viscose coupler was established using beam elements. The finite element model of the cotton-adhesive coupler is connected to the honeycomb aluminum block model, and the failure criteria and failure parameters of the beam element are set. The mechanical properties of the material were obtained through multi-level calibration tests of the cotton-adhesive coupler, and the finite element model was iteratively corrected based on the mechanical properties of the material to obtain a honeycomb aluminum partition adhesive coupler model for application in honeycomb aluminum barrier collision simulation.

2. The method according to claim 1, characterized in that, The establishment of an equivalent honeycomb aluminum block model includes: The origin of the coordinate system is selected as the modeling reference, and three two-dimensional shell elements representing one side of the honeycomb hole are established. A complete regular hexagonal honeycomb cell unit is generated by rotating and replicating around the center point; The regular hexagonal honeycomb cell units are arrayed and replicated along the length, width and height of the honeycomb aluminum block to construct a single honeycomb aluminum block; The single honeycomb aluminum block is copied to obtain two honeycomb aluminum blocks, which are connected to each other by the cotton adhesive coupling body.

3. The method according to claim 1, characterized in that, The finite element model of the cotton-viscose coupling body established using beam elements includes: A layer of beam units is arranged in the original partition plane. The cross-sectional shape of the beam units is consistent with the cross-sectional geometry of the honeycomb aluminum on both sides, and the node positions of the beam units correspond one-to-one with the node coordinates on the corresponding cross-section of the honeycomb aluminum blocks. Extending from the beam unit nodes within the original partition plane to both sides, a beam unit structure for connecting the honeycomb aluminum blocks is established.

4. The method according to claim 3, characterized in that, The connection between the finite element model of the cotton-adhesive coupler and the honeycomb aluminum block model includes: By using a common node method, the beam units extending on both sides are connected to the beam unit nodes and the corresponding nodes of the honeycomb aluminum blocks in the original partition plane, respectively.

5. The method according to claim 1, characterized in that, The method of obtaining material mechanical property parameters through multi-level calibration tests of cotton-viscose couplers includes: Static calibration tests were conducted on the cotton-viscose coupler to obtain the material's basic elasticity, plasticity, and failure parameters. Dynamic calibration tests were conducted on the cotton-viscose coupler to obtain the mechanical response and failure behavior parameters of the material under high strain rate. Conduct calibration tests on the combined structure to obtain the failure modes and failure parameters of the combined structure.

6. The method according to claim 5, characterized in that, The static calibration test of the cotton-viscose coupler was conducted to obtain the basic elasticity, plasticity, and failure parameters of the material, including: Preparation of cotton-viscose coupler samples for testing; The test specimen was subjected to a quasi-static uniaxial tensile test to obtain the yield stress, elastic modulus and failure strain. A torsion test was performed on the sample to obtain the torsional stiffness and shear modulus.

7. The method according to claim 5, characterized in that, The dynamic calibration test of the cotton-viscose coupler was conducted to obtain the mechanical response and failure behavior parameters of the material under high strain rates, including: Prepare a square cotton-cloth adhesive coupler sample for testing; Constrain the degree of freedom of the test sample in the plane normal direction; The central region of the test sample was dynamically impacted at different rates using a square impactor. Record the impact force displacement velocity history and failure process to obtain the failure mode and energy absorption characteristics of the coupled body under high strain rate.

8. The method according to claim 5, characterized in that, The calibration test of the combined structure to obtain the failure mode and failure parameters of the combined structure includes: A simplified I-shaped connection unit was prepared, consisting of two small honeycomb aluminum blocks and a cotton cloth adhesive coupler in the middle. A tangential shear test was conducted on the simplified I-shaped connection unit to measure its load-displacement curve deformation failure process and final failure mode. A normal peel test was performed on the simplified I-shaped connection unit to measure its load-displacement curve deformation failure process and final failure mode.

9. The method according to claim 1, characterized in that, The iterative correction of the finite element model based on the material mechanical property parameters includes: Establish simulation models corresponding to each level of calibration test; The material mechanical property parameters obtained from various calibration tests are substituted into the simulation model to calibrate the corresponding parameters of the beam element; Update the failure parameters of the beam element to make the deformation process and failure mode of the coupled body in the simulation consistent with the experimental observation results.

10. An electronic device, characterized in that, The electronic device includes one or more processors and one or more memories, wherein at least one piece of program code is stored in the one or more memories, and the at least one piece of program code is loaded and executed by the one or more processors to implement the method as described in any one of claims 1 to 9.

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