Layer-by-layer multi-scale calculation method and calculation system for composite honeycomb sandwich panels

Abstract

This invention discloses a layer-by-layer multi-scale calculation method and system for composite honeycomb sandwich panels, belonging to the field of computer-aided design technology. The method includes: S1, applying periodic boundary conditions to the microscale honeycomb sandwich cell model and processing it in a homogenization module; S2, setting displacement and / or load boundary conditions for the macroscale honeycomb sandwich panel model, and importing the stress from the microscale honeycomb sandwich cell model and the equivalent material properties of the macroscale honeycomb sandwich panel model; S3, using the virtual displacement principle to substitute the interpolation function of the macroscale displacement field into the macroscale honeycomb sandwich panel model, establishing a displacement finite element model corresponding to the layer-by-layer theory; S4, selecting the stress and strain values ​​at a Gaussian integration point of a certain element in the macroscale honeycomb sandwich panel model, and solving for the stress and strain values ​​of the microscale honeycomb sandwich cell model under this state. This invention enables efficient calculation of the model by transferring material parameters across scales.

Description

Technical Field

[0001] This invention belongs to the field of computer-aided design technology, and in particular relates to a layer-by-layer multi-scale calculation method and system for composite honeycomb sandwich panels. Background Technology

[0002] In recent years, with the rapid development of aerospace technology, spacecraft missions have become increasingly diversified and complex, leading to a rapid increase in demand. As demand continues to rise, the load-bearing requirements and economic benefits of spacecraft themselves are also increasing. Due to their excellent load-bearing capacity, high specific stiffness and specific strength, and lightweight configuration compared to other material structures, honeycomb sandwich panels are widely used in spacecraft construction.

[0003] Finite element method (FEM) software is now widely used for 1:1 scale modeling of honeycomb sandwich structures. However, 1:1 FEM models that include detailed microstructures of the sandwich structure face problems such as a large number of model elements, long computation time, and low computational efficiency. Summary of the Invention

[0004] Technical issues This invention provides a method for cross-scale calculation of arbitrary layup angles and number of layers in a honeycomb sandwich panel model; it enables efficient calculation of the model by transferring material parameters across scales.

[0005] Technical solution

[0006] The first objective of this invention is to provide a layer-by-layer multi-scale calculation method for composite honeycomb sandwich panels, comprising the following steps: S1. Apply periodic boundary conditions to the microscale honeycomb sandwich cell model and process it in the homogenization module. First, gradually expand the displacement field, and then obtain the stress of the microscale honeycomb sandwich cell model and the equivalent material properties of the macroscale honeycomb sandwich panel model through the chain rule. S2. Set the displacement and / or load boundary conditions of the macro-scale honeycomb sandwich panel model, and import the stress of the micro-scale honeycomb sandwich cell model and the equivalent material properties of the macro-scale honeycomb sandwich panel model. S3. Using the principle of virtual displacement, the interpolation function of the macroscopic displacement field is substituted into the macroscopic scale honeycomb sandwich panel model to establish a displacement finite element model corresponding to the layer-by-layer theory, and the displacement and stress-strain values ​​of the macroscopic scale honeycomb sandwich panel model are obtained. S4: Select the stress and strain value at a Gaussian integration point of a certain element in the macro-scale honeycomb sandwich panel model, and solve for the stress and strain value of the micro-scale honeycomb sandwich cell model under this state.

[0007] The second objective of this invention is to provide a layer-by-layer multi-scale calculation system for composite honeycomb sandwich panels. Homogenization module: Apply periodic boundary conditions to the microscale honeycomb sandwich cell model and process it in the homogenization module. First, the displacement field is gradually expanded, and then the stress of the microscale honeycomb sandwich cell model and the equivalent material properties of the macroscale honeycomb sandwich panel model are obtained through the chain rule. Setting module: Sets the displacement and / or load boundary conditions of the macro-scale honeycomb sandwich panel model, and imports the stress of the micro-scale honeycomb sandwich cell model and the equivalent material properties of the macro-scale honeycomb sandwich panel model; Model building module: Using the principle of virtual displacement, the interpolation function of the macroscopic displacement field is substituted into the macroscopic scale honeycomb sandwich panel model to establish a displacement finite element model corresponding to the layer-by-layer theory, and the displacement and stress-strain values ​​of the macroscopic scale honeycomb sandwich panel model are obtained. Calculation module: Select the stress and strain value at a Gaussian integration point of a certain element in the macro-scale honeycomb sandwich panel model, and solve for the stress and strain value of the micro-scale honeycomb sandwich cell model under this state.

[0008] The third objective of this invention is to provide an information data processing terminal for implementing the layer-by-layer multi-scale calculation method for the above-mentioned composite honeycomb sandwich panel.

[0009] A fourth objective of this invention is to provide a computer-readable storage medium including instructions that, when executed on a computer, cause the computer to perform the aforementioned layer-by-layer multi-scale calculation method for composite honeycomb sandwich panels.

[0010] The advantages and positive effects of this invention are as follows: By adopting the above technical solution, the present invention has the following technical effects: This invention reads a honeycomb sandwich unit cell model into a multi-scale computational model derived from layer-by-layer theoretical analysis. First, periodic boundary conditions are applied to the unit cell model, and the equivalent material parameters of the honeycomb sandwich unit cell model are obtained through the program's homogenization module. By setting displacement / load boundary conditions, the macroscopic model is solved using a layer-by-layer method to obtain the displacement, stress, and strain of the macroscopic composite honeycomb sandwich panel model. Finally, the microscopic model is post-processed based on the stress and strain of the macroscopic model.

[0011] This invention establishes a layer-by-layer multi-scale calculation method for composite honeycomb sandwich panels, which can realize cross-scale calculation of honeycomb sandwich panel models with different layup angles and number of layers, and can also achieve efficient calculation of the model by using the layer-by-layer method. Attached Figure Description

[0012] Figure 1 This is a flowchart of a preferred embodiment of the present invention; Figure 2 This is a model diagram of a composite honeycomb sandwich panel at a macroscopic scale in a preferred embodiment of the present invention; Figure 3 This is a representative volumetric unit model diagram with detailed honeycomb sandwich structure at the microscale in a preferred embodiment of the present invention. Detailed Implementation

[0013] To further understand the invention's content, features, and effects, the following embodiments are provided, along with detailed descriptions in conjunction with the accompanying drawings. The technical solutions in the embodiments of the invention will be clearly and completely described below with reference to the flowcharts. Obviously, the described embodiments are merely some, not all, of the embodiments of the invention. All other embodiments obtained by those skilled in the art based on the embodiments of the invention without creative effort are within the scope of protection of the invention.

[0014] It will be apparent to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above, and that the invention can be implemented in other specific forms without departing from its spirit or essential characteristics. Therefore, the embodiments should be considered in all respects as exemplary and non-limiting, and the scope of the invention is defined by the appended claims rather than the foregoing description. Thus, all variations falling within the meaning and scope of equivalents of the claims are intended to be included within the present invention. No reference numerals in the claims should be construed as limiting the scope of the claims.

[0015] Furthermore, it should be understood that although this specification describes embodiments, not every embodiment contains only one independent technical solution. This narrative style is merely for clarity. Those skilled in the art should consider the specification as a whole, and the technical solutions in each embodiment can also be appropriately combined to form other embodiments that can be understood by those skilled in the art.

[0016] Please see Figures 1 to 3 A layer-by-layer multi-scale calculation method for composite honeycomb sandwich panels, wherein the multi-scale includes macroscopic and microscopic scales; the macroscopic scale is the composite honeycomb sandwich panel model ( Figure 2 The right-hand image shows a representative volumetric unit model with detailed honeycomb sandwich structure at the microscale. Figure 3 (See the right-hand diagram). Taking a multi-layer honeycomb sandwich core as an example, the process includes the following four steps: S1. Apply periodic boundary conditions to the microscale honeycomb sandwich cell model and process them in the homogenization module. First, gradually expand the displacement field, and then obtain the stress of the microscale honeycomb sandwich cell model and the equivalent material properties of the macroscale honeycomb sandwich panel model through the chain rule; specifically: S101: Import data from a microscale honeycomb sandwich cell model; the data from the microscale honeycomb sandwich cell model includes cell node information and boundary condition information; the boundary condition information includes forces and / or constraints applied to the model; S102: Apply periodic boundary conditions to the microscale honeycomb sandwich cell model and process it in the homogenization module. The periodic boundary conditions are as follows: (1); Where: i', j', k' are the displacements of the image point in the x, y, and z directions, respectively; i, j, k are the displacements of the original node in the x, y, and z directions, respectively; V x V y V z These represent the coordinate differences between the image point and the original node in each direction; ε x , ε y , ε z γ xy γ xz γ yz For each strain component; Then the displacement field is gradually expanded according to the following formula (2): (2); Where: x represents the position vector in the macroscopic solution domain, y represents the position vector in the microscopic unit cell domain, ξ represents the positive parameter; U is the displacement; Then, the stress σ of the microscale honeycomb sandwich cell model is obtained through the chain rule: (3); S2, setting displacement and / or load boundary conditions for the macro-scale honeycomb sandwich panel model, and importing the stress from the micro-scale honeycomb sandwich cell model and the equivalent material properties of the macro-scale honeycomb sandwich panel model; S2 includes: reading in the finite element data of the macro-scale composite honeycomb sandwich panel structure; specifically including: S201: Set the number of layers and layup angle of the macro-scale composite honeycomb sandwich panel; S202: Imparts equivalent material properties to macroscopic composite honeycomb sandwich panels; S203: Read in the boundary condition information of the macro-scale composite honeycomb sandwich panel model; S3. Using the principle of virtual displacement, the interpolation function of the macroscopic displacement field is substituted into the macroscopic scale honeycomb sandwich panel model to establish a displacement finite element model corresponding to the layer-by-layer theory, and the displacement and stress-strain values ​​of the macroscopic scale honeycomb sandwich panel model are obtained. Specifically, it includes: S301: The displacement field of the layer-by-layer method is given by the following equation. (4); In the formula, α represents the displacement components in the directions x, y, and z; It is a continuous function of the thickness coordinate z, where N is the mathematical layer number; U αk This represents the value on the k-th plane; c refers to the macroscopic scale. Assuming the displacement field is interpolated to (5); In the formula, ele is the number of nodes in each two-dimensional unit, and U αkm Ψ represents the displacement value at the m-th node of the k-th plane in a two-dimensional finite element model of the plate element. m It is the two-dimensional Lagrange interpolation polynomial associated with the j-th node of the two-dimensional finite element, where t is time; S302: The constitutive equation for the μth layer of the composite honeycomb sandwich panel is: (6); The governing equations for the layer-by-layer method are as follows: (7); The stiffness matrix is ​​given by the following equation.

[0017]

[0018]

[0019] The equivalent stiffness coefficient is given by the following formula.

[0020] Where: t and b are the relative distances along the z-axis; S303: Obtain the finite element formulation of the layer-by-layer theoretical equations for the composite honeycomb sandwich structure, and calculate the displacement and strain of the macroscopic composite honeycomb sandwich panel model.

[0021] S4: Select the stress and strain value at a Gaussian integration point of a certain element in the macro-scale honeycomb sandwich panel model, and solve for the stress and strain value of the micro-scale honeycomb sandwich cell model under this state.

[0022] The steps of this application are explained in detail below through a specific case: Step 1: Import the data of the pre-built honeycomb sandwich panel.

[0023] Step 1.1: Read in the element node information (including the element node number and node geometric position coordinates).

[0024] Table 1: Parameters of micro-cell materials in honeycomb sandwich cores

[0025] Step 1.2: Read in the boundary condition information of the cell; Step 2: The honeycomb sandwich cell is processed in the homogenization module, and the displacement field is gradually spread out first;

[0026] Then, the stress of the honeycomb sandwich cell model is obtained through the chain rule:

[0027] Step 3: Read in the limited metadata of the structure.

[0028] Step 3.1: Select a multi-layer honeycomb sandwich panel with 16 layers and a layup angle of 0°; Step 3.2: Assigning properties to the honeycomb sandwich material; Step 3.3: Read in the boundary condition information of the structure.

[0029] Step 4: Using the principle of virtual displacement, the interpolation function of the macroscopic displacement field is substituted into the sandwich panel model to establish a displacement finite element model corresponding to the layer-by-layer theory.

[0030] Step 4.1: The displacement field of the layer-by-layer method is given by the following equation: ; Step 4.2: The constitutive equation for the μth layer of the composite laminate is:

[0031] Step 4.3: Obtain the finite element formulation of the theoretical motion equations of the laminated plate structure layer by layer, and calculate the displacement and strain of the macroscopic composite honeycomb sandwich panel model.

[0032] Table 2 Macroscopic displacements of honeycomb sandwich panels obtained by the layer-by-layer multi-scale method

[0033] In the table, Ux represents the magnitude of displacement in the x-direction, Uy represents the magnitude of displacement in the y-direction, and Uz represents the magnitude of displacement in the z-direction. Table 3 Macroscopic strain of honeycomb sandwich panels obtained by the layer-by-layer multi-scale method

[0034] In the table, SIGXX represents the normal strain in the x-direction, SIGYY represents the normal strain in the y-direction, SIGZZ represents the normal strain in the z-direction, SIGXY represents the shear strain in the xy-direction, SIGXZ represents the shear strain in the xz-direction, and SIGYZ represents the shear strain in the yz-direction.

[0035] Step 5: Finally, select the stress and strain of a certain element in the macroscopic scale model and solve for the microscopic scale stress and strain under this state.

[0036] A layer-by-layer multi-scale calculation system for composite honeycomb sandwich panels includes: Homogenization module: Applying periodic boundary conditions to the microscale honeycomb sandwich cell model and processing it within the homogenization module, first gradually expanding the displacement field, then obtaining the stress of the microscale honeycomb sandwich cell model and the equivalent material properties of the macroscale honeycomb sandwich panel model through the chain rule; specifically: S101: Import data from a microscale honeycomb sandwich cell model; the data from the microscale honeycomb sandwich cell model includes cell node information and boundary condition information; the boundary condition information includes forces and / or constraints applied to the model; S102: Apply periodic boundary conditions to the microscale honeycomb sandwich cell model and process it in the homogenization module. The periodic boundary conditions are as follows: (1); Where: i', j', k' are the displacements of the image point in the x, y, and z directions, respectively; i, j, k are the displacements of the original node in the x, y, and z directions, respectively; V x V y V z These represent the coordinate differences between the image point and the original node in each direction; ε x , ε y , ε z γ xy γ xz γ yz For each strain component; Then the displacement field is gradually expanded according to the following formula (2): (2); Where: x represents the position vector in the macroscopic solution domain, y represents the position vector in the microscopic unit cell domain, ξ represents the positive parameter; U is the displacement; Then, the stress σ of the microscale honeycomb sandwich cell model is obtained through the chain rule: (3); The configuration module sets the displacement and / or load boundary conditions for the macroscale honeycomb sandwich panel model, and imports the stress from the microscale honeycomb sandwich cell model and the equivalent material properties of the macroscale honeycomb sandwich panel model. The configuration includes reading in the finite element data of the macroscale composite honeycomb sandwich panel structure; specifically: S201: Set the number of layers and layup angle of the macro-scale composite honeycomb sandwich panel; S202: Imparts equivalent material properties to macroscopic composite honeycomb sandwich panels; S203: Read in the boundary condition information of the macro-scale composite honeycomb sandwich panel model; Model building module: Using the principle of virtual displacement, the interpolation function of the macroscopic displacement field is substituted into the macroscopic scale honeycomb sandwich panel model to establish a displacement finite element model corresponding to the layer-by-layer theory, and the displacement and stress-strain values ​​of the macroscopic scale honeycomb sandwich panel model are obtained. Specifically, it includes: S301: The displacement field of the layer-by-layer method is given by the following equation. (4); In the formula, α represents the displacement components in the directions x, y, and z; ɸ k It is a continuous function of the thickness coordinate z, where N is the mathematical layer number; U αk This represents the value on the k-th plane; c refers to the macroscopic scale. Assuming the displacement field is interpolated to (5); In the formula, ele is the number of nodes in each two-dimensional unit, and U αkm Ψ represents the displacement value at the m-th node of the k-th plane in a two-dimensional finite element model of the plate element. m It is the two-dimensional Lagrange interpolation polynomial associated with the j-th node of the two-dimensional finite element, where t is time; S302: The constitutive equation for the μth layer of the composite honeycomb sandwich panel is: (6); The governing equations for the layer-by-layer method are as follows: (7); The stiffness matrix is ​​given by the following equation.

[0037]

[0038]

[0039] The equivalent stiffness coefficient is given by the following formula.

[0040] Where: t and b are the relative distances along the z-axis; S303: Obtain the finite element formulation of the layer-by-layer theoretical equations for the composite honeycomb sandwich structure, and calculate the displacement and strain of the macroscopic composite honeycomb sandwich panel model.

[0041] Calculation module: Select the stress and strain value at a Gaussian integration point of a certain element in the macro-scale honeycomb sandwich panel model, and solve for the stress and strain value of the micro-scale honeycomb sandwich cell model under this state.

[0042] An information data processing terminal for implementing the layer-by-layer multi-scale calculation method of the above-mentioned composite honeycomb sandwich panel.

[0043] A computer-readable storage medium includes instructions that, when executed on a computer, cause the computer to perform the aforementioned layer-by-layer multi-scale calculation method for composite honeycomb sandwich panels.

[0044] In the above embodiments, implementation can be achieved, in whole or in part, through software, hardware, firmware, or any combination thereof. When implemented, in whole or in part, as a computer program product, the computer program product includes one or more computer instructions. When the computer program instructions are loaded or executed on a computer, all or part of the processes or functions described in the embodiments of the present invention are generated. The computer can be a general-purpose computer, a special-purpose computer, a computer network, or other programmable device. The computer instructions can be stored in a computer-readable storage medium or transmitted from one computer-readable storage medium to another. For example, the computer instructions can be transmitted from one website, computer, server, or data center to another website, computer, server, or data center via wired (e.g., coaxial cable, fiber optic, digital subscriber line (DSL)) or wireless (e.g., infrared, wireless, microwave, etc.) means. The computer-readable storage medium can be any available medium that a computer can access or a data storage device such as a server or data center that integrates one or more available media. The available medium can be a magnetic medium (e.g., floppy disk, hard disk, magnetic tape), an optical medium (e.g., DVD), or a semiconductor medium (e.g., a solid-state drive (SSD)).

[0045] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention in any way. Any simple modifications, equivalent changes, and alterations made to the above embodiments based on the technical essence of the present invention shall fall within the scope of the technical solution of the present invention.

Claims

1. A layer-by-layer multi-scale calculation method for composite honeycomb sandwich panels, characterized in that, Includes the following steps: S1. Apply periodic boundary conditions to the microscale honeycomb sandwich cell model and process them in the homogenization module. First, gradually expand the displacement field, and then obtain the stress of the microscale honeycomb sandwich cell model and the equivalent material properties of the macroscale honeycomb sandwich panel model through the chain rule; specifically: S101: Import data from a microscale honeycomb sandwich cell model; the data from the microscale honeycomb sandwich cell model includes cell node information and boundary condition information; the boundary condition information includes forces and / or constraints applied to the model; S102: Apply periodic boundary conditions to the microscale honeycomb sandwich cell model and process them in the homogenization module. The periodic boundary conditions are as follows: （1）； Where: i', j', k' are the displacements of the image point in the x, y, and z directions, respectively; i, j, k are the displacements of the original node in the x, y, and z directions, respectively; V x V y V z These represent the coordinate differences between the image point and the original node in each direction; ε x , ε y , ε z γ xy γ xz γ yz For each strain component; Then the displacement field is gradually expanded according to the following formula (2): （2）； Where: x represents the position vector in the macroscopic solution domain, y represents the position vector in the microscopic unit cell domain, ξ represents the positive parameter; U is the displacement; Then, the stress σ of the microscale honeycomb sandwich cell model is obtained through the chain rule: （3）； S2. Set the displacement and / or load boundary conditions of the macro-scale honeycomb sandwich panel model, and import the stress of the micro-scale honeycomb sandwich cell model and the equivalent material properties of the macro-scale honeycomb sandwich panel model. S3. Using the principle of virtual displacement, the interpolation function of the macroscopic displacement field is substituted into the macroscopic-scale honeycomb sandwich panel model to establish a displacement finite element model corresponding to the layer-by-layer theory, obtaining the displacement and stress-strain values ​​of the macroscopic-scale honeycomb sandwich panel model; specifically including: S301: The displacement field of the layer-by-layer method is given by the following equation. （4）； In the formula, α represents the displacement components in the directions x, y, and z; It is a continuous function of the thickness coordinate z, where N is the mathematical layer number; U αk This represents the value on the k-th plane; c refers to the macroscopic scale. Assuming the displacement field is interpolated to （5）； In the formula, ele is the number of nodes in each two-dimensional unit, and U αkm Ψ represents the displacement value at the m-th node of the k-th plane in a two-dimensional finite element model of the plate element. m It is the two-dimensional Lagrange interpolation polynomial associated with the j-th node of the two-dimensional finite element, where t is time; S302: The constitutive equation for the μth layer of the composite honeycomb sandwich panel is: （6）； The governing equations for the layer-by-layer method are as follows: （7）； The stiffness matrix is ​​given by the following equation. ； ； ； The equivalent stiffness coefficient is given by the following formula. ； Where: t and b are the relative distances along the z-axis; S303: Obtain the finite element formulation of the layer-by-layer theoretical equation of the composite honeycomb sandwich structure, and calculate the displacement and strain of the macroscopic composite honeycomb sandwich panel model. S4: Select the stress and strain value at a Gaussian integration point of a certain element in the macro-scale honeycomb sandwich panel model, and solve for the stress and strain value of the micro-scale honeycomb sandwich cell model under this state.

2. The layer-by-layer multi-scale calculation method for composite honeycomb sandwich panels according to claim 1, characterized in that, S2 includes: Read in finite metadata of macroscale composite honeycomb sandwich panel structures; specifically including: S201: Set the number of layers and layup angle of the macro-scale composite honeycomb sandwich panel; S202: Imparts equivalent material properties to macroscopic composite honeycomb sandwich panels; S203: Read in the boundary condition information of the macro-scale composite honeycomb sandwich panel model.

3. A layer-by-layer multi-scale calculation system for composite honeycomb sandwich panels, characterized in that, include: Homogenization module: Periodic boundary conditions are applied to the microscale honeycomb sandwich cell model, and the homogenization process is performed in the homogenization module. First, the displacement field is gradually expanded, and then the stress of the microscale honeycomb sandwich cell model and the equivalent material properties of the macroscale honeycomb sandwich panel model are obtained through the chain rule. The specific process of homogenization is as follows: S101: Import data from a microscale honeycomb sandwich cell model; the data from the microscale honeycomb sandwich cell model includes cell node information and boundary condition information; the boundary condition information includes forces and / or constraints applied to the model; S102: Apply periodic boundary conditions to the microscale honeycomb sandwich cell model and process them in the homogenization module. The periodic boundary conditions are as follows: （1）； Where: i', j', k' are the displacements of the image point in the x, y, and z directions, respectively; i, j, k are the displacements of the original node in the x, y, and z directions, respectively; V x V y V z These represent the coordinate differences between the image point and the original node in each direction; ε x , ε y , ε z γ xy γ xz γ yz For each strain component; Then the displacement field is gradually expanded according to the following formula (2): （2）； Where: x represents the position vector in the macroscopic solution domain, y represents the position vector in the microscopic unit cell domain, ξ represents the positive parameter; U is the displacement; Then, the stress σ of the microscale honeycomb sandwich cell model is obtained through the chain rule: （3）； Setting module: Sets the displacement and / or load boundary conditions of the macro-scale honeycomb sandwich panel model, and imports the stress of the micro-scale honeycomb sandwich cell model and the equivalent material properties of the macro-scale honeycomb sandwich panel model; Model building module: Using the principle of virtual displacement, the interpolation function of the macroscopic displacement field is substituted into the macroscopic-scale honeycomb sandwich panel model to establish a displacement finite element model corresponding to the layer-by-layer theory, obtaining the displacement and stress-strain values ​​of the macroscopic-scale honeycomb sandwich panel model; specifically including: S301: The displacement field of the layer-by-layer method is given by the following equation. （4）； In the formula, α represents the displacement components in the directions x, y, and z; It is a continuous function of the thickness coordinate z, where N is the mathematical layer number; U αk This represents the value on the k-th plane; c refers to the macroscopic scale. Assuming the displacement field is interpolated to （5）； In the formula, ele is the number of nodes in each two-dimensional unit, and U αkm Ψ represents the displacement value at the m-th node of the k-th plane in a two-dimensional finite element model of the plate element. m It is the two-dimensional Lagrange interpolation polynomial associated with the j-th node of the two-dimensional finite element, where t is time; S302: The constitutive equation for the μth layer of the composite honeycomb sandwich panel is: （6）； The governing equations for the layer-by-layer method are as follows: （7）； The stiffness matrix is ​​given by the following equation. ； ； ； The equivalent stiffness coefficient is given by the following formula. ； Where: t and b are the relative distances along the z-axis; S303: Obtain the finite element formulation of the layer-by-layer theoretical equation of the composite honeycomb sandwich structure, and calculate the displacement and strain of the macroscopic composite honeycomb sandwich panel model. Calculation module: Select the stress and strain value at a Gaussian integration point of a certain element in the macro-scale honeycomb sandwich panel model, and solve for the stress and strain value of the micro-scale honeycomb sandwich cell model under this state.

4. The layer-by-layer multi-scale calculation system for composite honeycomb sandwich panels according to claim 3, characterized in that, The module setup process includes: reading in finite metadata of macro-scale composite honeycomb sandwich panel structures; specifically: S201: Set the number of layers and layup angle of the macro-scale composite honeycomb sandwich panel; S202: Imparts equivalent material properties to macroscopic composite honeycomb sandwich panels; S203: Read in the boundary condition information of the macro-scale composite honeycomb sandwich panel model.

5. An information data processing terminal for implementing the layer-by-layer multi-scale calculation method for composite honeycomb sandwich panels according to any one of claims 1-2.

6. A computer-readable storage medium comprising instructions, when executed on a computer, causing the computer to perform a layer-by-layer multi-scale calculation method for composite honeycomb sandwich panels as described in any one of claims 1-2.

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