A method for predicting the mechanical behavior of a laminated lattice-reinforced composite

Abstract

The application discloses a kind of plate system lattice reinforced composite material mechanical behavior prediction method, belong to novel lattice structure lattice unit model field.Specific as follows:1) establish triangle plate model;2) to each triangle plate in triangle plate model thickening, obtain 1 / 8 plate system lattice unit model;3) 1 / 8 plate system lattice unit model is sequentially with XOY, YOZ, ZOX plane mirror symmetry, obtain first plate system lattice structure model;4) amplification first plate system lattice structure model obtains second plate system lattice structure model;5) second plate system lattice structure model is subtracted from the cube model with side length 2L, obtain matrix material model;Matrix material model is subtracted from the above-mentioned cube model, obtain reinforcing material model;Assemble after plate system lattice structure reinforced composite material model;6) grid division, and apply tensile boundary condition;Respectively input material attribute, carry out numerical simulation to the mechanical behavior in the tensile process of plate system lattice structure reinforced composite material.

Description

TECHNICAL FIELD

[0001] The application belongs to the field of novel lattice structure lattice unit model design, and particularly relates to a mechanical behavior prediction method of plate lattice reinforced composite materials. BACKGROUND

[0002] In the field of engineering design, the mechanical behavior of lattice structure reinforced composite materials is a crucial research topic. The geometry of the lattice structure has a significant impact on the stress-strain distribution of the system. Although traditional experimental measurement methods can qualitatively reflect the load transfer and two-phase deformation to some extent, they have obvious limitations and are difficult to measure the influence of different shapes of lattice structures on the stress-strain distribution and mechanical properties of the system systematically and comprehensively.

[0003] In recent years, with the rapid development of computer technology, finite element simulation technology has been increasingly applied in the simulation of the mechanical behavior of plate lattice structures, and has achieved relatively accurate performance prediction results. However, existing finite element simulation methods still have some shortcomings when facing different shapes of plate lattice structures, such as low computational efficiency and limited ability to handle complex geometries. In order to overcome these shortcomings, a new modeling method for plate lattice structure lattice units needs to be designed in combination with finite element simulation technology. SUMMARY

[0004] The purpose of the present application is to provide a mechanical behavior prediction method of plate lattice reinforced composite materials in view of the current situation of difficulty in modeling the shape of plate lattice structure lattice units in the prior art. The present application can create plate lattice structures of various shapes. With the help of finite element simulation technology, the mechanical behavior of plate lattice structure reinforced composite materials can be predicted, and the mechanical properties of plate lattice structures can be calculated.

[0005] The specific technical solutions adopted by the present application are as follows:

[0006] The present application provides a mechanical behavior prediction method of plate lattice reinforced composite materials, and the specific steps are as follows:

[0007] S1: creating a cubic model CUBIC with an edge length of L in a three-dimensional modeling software;

[0008] S2: establishing a triangular plate model in the three-dimensional modeling software based on the number of plates N;

[0009] S3: thickening each triangular plate in the triangular plate model to obtain a 1 / 8 plate lattice unit model;

[0010] S4: mirror symmetrizing the 1 / 8 plate lattice unit model obtained in step S3 in the XOY plane of the Cartesian coordinate system, combining and then mirror symmetrizing in the YOZ plane, combining and then mirror symmetrizing in the ZOX plane to obtain a first plate lattice structure model;

[0011] S5: doubling the first plate lattice structure model obtained in step S4 along the X, Y and Z axes of the Cartesian coordinate system to obtain a second plate lattice structure model;

[0012] S6: establishing a cubic model BIGCUBIC with a side length of 2L; performing a body subtraction operation in the modeling software to subtract the second plate lattice structure model from the cubic model BIGCUBIC to obtain a matrix material model; subtracting the matrix material model from the cubic model BIGCUBIC to obtain a reinforcing body material model;

[0013] S6: assembling the matrix material model and the reinforcing body material model to obtain a plate lattice structure reinforced composite material model;

[0014] S7: performing mesh division on the plate lattice structure reinforced composite material model and applying a tensile boundary condition; inputting the material properties of the matrix material and the reinforcing body material, respectively, to numerically simulate the mechanical behavior of the plate lattice structure reinforced composite material in the tensile process to obtain the Young's modulus, Poisson's ratio, strength and elongation of the plate lattice structure composite material.

[0015] As a preferred, the three-dimensional modeling software includes AutoCAD, Blender, Rhino, Abaqus or Ansys software.

[0016] As a preferred, the 8 vertices of the cubic model CUBIC are (0, 0, 0), (0, 0, L), (0, L, L), (0, L, 0), (L, 0, 0), (L, 0, L), (L, L, L), (L, L, 0), respectively; the 8 vertices of the cubic model BIGCUBIC are (-L, -L, -L), (-L, -L, L), (-L, L, L), (-L, L, -L), (L, -L, -L), (L, -L, L), (L, L, L), (L, L, -L), respectively.

[0017] As a preferred, the triangular plate model establishing method in step S2 is as follows:

[0018] S201: input three vertex coordinates, which are all located on the surface of the cubic model CUBIC, and determine a triangular plate according to the three vertices;

[0019] S202: based on the number of plates N, repeat step S201 N times to determine N triangular plates; the N triangular plates are combined to obtain a triangular plate model.

[0020] As preferred, in step S3, each triangular plate is thickened by T / 2 along its positive and negative normal respectively, so that the thickness of the plate is T, obtaining a 1 / 8 plate series lattice unit model.

[0021] As preferred, step S4 is specifically as follows:

[0022] S401: Copy one of the 1 / 8 plate series lattice unit models, mirror symmetric in the XOY plane of the Cartesian coordinate system to obtain a 1 / 8 plate series lattice unit symmetric model; merge the 1 / 8 plate series lattice unit model and the 1 / 8 plate series lattice unit symmetric model to obtain a 1 / 4 plate series lattice unit model;

[0023] S402: Copy one of the 1 / 4 plate series lattice unit models, mirror symmetric in the YOZ plane of the Cartesian coordinate system to obtain a 1 / 4 plate series lattice unit symmetric model; merge the 1 / 4 plate series lattice unit model and the 1 / 4 plate series lattice unit symmetric model to obtain a 1 / 2 plate series lattice unit model;

[0024] S403: Copy one of the 1 / 2 plate series lattice unit models, mirror symmetric in the ZOX plane of the Cartesian coordinate system to obtain a 1 / 2 plate series lattice unit symmetric model; merge the 1 / 2 plate series lattice unit model and the 1 / 2 plate series lattice unit symmetric model to obtain a first plate series lattice structure model.

[0025] As preferred, step S5 is specifically as follows:

[0026] S501: Copy 7 of the first plate series lattice structure models and move them along the vectors (0, 0, -2L), (0, -2L, -2L), (0, -2L, 0), (-2L, 0, 0), (-2L, 0, -2L), (-2L, -2L, -2L), and (-2L, -2L, 0) respectively;

[0027] S502: Merge the first plate series lattice structure model and the models moved in step S501 to obtain a second plate series lattice structure model.

[0028] As preferred, in the mesh division in step S7, the mesh type is a 4-node tetrahedral element, and the total number of mesh elements is not less than 500,000.

[0029] As preferred, in step S7, the tensile boundary condition is set as follows:

[0030] S701: Set the value range of the maximum tensile strain E to be 0.1% to 10%; set the value range of the tensile rate S to be 0.0001s -1 to 0.01s -1 .

[0031] S702: If the stretching direction is the X direction, the X direction displacement of all the grid nodes on the X=-L plane is constrained to be 0, and the X direction displacement of all the grid nodes on the X=L plane is applied, and the displacement amount is 2LxE; if the stretching direction is the Y direction, the Y direction displacement of all the grid nodes on the Y=-L plane is constrained to be 0, and the Y direction displacement of all the grid nodes on the Y=L plane is applied, and the displacement amount is 2LxE; if the stretching direction is the Z direction, the Z direction displacement of all the grid nodes on the Z=-L plane is constrained to be 0, and the Z direction displacement of all the grid nodes on the Z=L plane is applied, and the displacement amount is 2LxE.

[0032] Preferably, the numerical simulation in step S7 is performed by using ABAQUS, ANSYS or Comsol finite element software.

[0033] Compared with the prior art, the present application has the following beneficial effects:

[0034] (1) The method provided by the present application can generate a plate lattice structure reinforced composite material model with various shapes and close to the real shape of industrial production by setting the plate model position and spatial orientation, and has wide applicability. By calculating the mechanical behavior under the load condition, the internal stress and strain distribution of the plate lattice structure reinforced composite material can be revealed, which not only has important academic significance, but also provides guidance for the structural design of industrial materials.

[0035] (2) The method provided by the present application is convenient to model and easy to operate, and only a small number of parameters such as the number of plates, node information and thickness of the plates need to be controlled. BRIEF DESCRIPTION OF DRAWINGS

[0036] Figure 1 Triangle plate model established for example 1;

[0037] Figure 2 1 / 8 plate lattice unit model established for example 1;

[0038] Figure 3 First plate lattice structure model UNIT established for example 1;

[0039] Figure 4 Second plate lattice structure model BIGUNIT established for example 1;

[0040] Figure 5 Matrix material model MATRIX established for example 1;

[0041] Figure 6 Reinforcement material model REINFORCEMENT established for example 1;

[0042] Figure 7COMPOSITE, which is a model of the lattice structure reinforced composite material established for example 1;

[0043] Figure 8 STRESS-STRAIN RELATIONSHIP FOR 6061 ALUMINUM IN EXAMPLE 1;

[0044] Figure 9 STRESS CLOUD FOR LATTICE STRUCTURE REINFORCED COMPOSITE MATERIAL IN EXAMPLE 1;

[0045] Figure 10 SIMULATED STRESS-STRAIN CURVE FOR LATTICE STRUCTURE REINFORCED COMPOSITE MATERIAL IN EXAMPLE 1. DETAILED DESCRIPTION

[0046] The present application will be further described and illustrated below in conjunction with the accompanying drawings and specific embodiments. The technical features of each embodiment in the present application can be combined accordingly without conflict.

[0047] The present application provides a method for predicting the mechanical behavior of a lattice structure reinforced composite material, and the specific steps are as follows:

[0048] I. Establishing a cubic model CUBIC

[0049] A cubic model CUBIC with an edge length of L is created in a three-dimensional modeling software, and the eight vertices of the cubic model CUBIC are (0, 0, 0), (0, 0, L), (0, L, L), (0, L, 0), (L, 0, 0), (L, 0, L), (L, L, L), and (L, L, 0).

[0050] II. Establishing a triangular plate model

[0051] (1) In the three-dimensional modeling software, select a triangular plate and input the number of plates N of the plate model; determine the plate thickness T.

[0052] (2) Input the three vertex coordinates P1 i (x1 i , y1 i , z1 i ), P2 i (x2 i , y2 i , z2 i ), and P3 i (x3 i , y3 i , z3 i ) of the i-th plate, i = 1, 2, …, N. The three vertices of each plate are located on the surface of the cubic CUBIC, and a triangular plate is determined according to the three vertices;

[0053] (3) Repeat step (2) N times based on the number of plates N to determine N triangular plates; the N triangular plates are combined to obtain a triangular plate model.

[0054] The three-dimensional modeling software can be AutoCAD, Blender, Rhino, Abaqus or Ansys software.

[0055] III. Establishing a 1 / 8 plate lattice unit model

[0056] Input the plate thickness T in the three-dimensional modeling software, so that each triangular plate is thickened by T / 2 along its positive and negative normal directions respectively, to obtain a 1 / 8 plate lattice unit model.

[0057] IV. Establishing a first plate lattice structure model UNIT

[0058] (1) Copy 1 of the 1 / 8 plate lattice unit model obtained in step three, mirror symmetrically in the XOY plane in the Cartesian coordinate system to obtain a 1 / 8 plate lattice unit symmetric model; combine the 1 / 8 plate lattice unit model and the 1 / 8 plate lattice unit symmetric model to obtain a 1 / 4 plate lattice unit model;

[0059] (2) Copy 1 of the 1 / 4 plate lattice unit model obtained in the above step, mirror symmetrically in the YOZ plane in the Cartesian coordinate system to obtain a 1 / 4 plate lattice unit symmetric model; combine the 1 / 4 plate lattice unit model and the 1 / 4 plate lattice unit symmetric model to obtain a 1 / 2 plate lattice unit model;

[0060] (3) Copy 1 of the 1 / 2 plate lattice unit model obtained in the above step, mirror symmetrically in the ZOX plane in the Cartesian coordinate system to obtain a 1 / 2 plate lattice unit symmetric model; combine the 1 / 2 plate lattice unit model and the 1 / 2 plate lattice unit symmetric model to obtain a first plate lattice structure model UNIT.

[0061] V. Establishing a second plate lattice structure model BIGUNIT

[0062] (1) Copy 7 of the first plate lattice structure model UNIT obtained in step four, and move along the vectors (0, 0, -2L), (0, -2L, -2L), (0, -2L, 0), (-2L, 0, 0), (-2L, 0, -2L), (-2L, -2L, -2L), (-2L, -2L, 0) respectively;

[0063] (2) Combine the first plate lattice structure model and the models moved in the above step to obtain a second plate lattice structure model BIGUNIT.

[0064] Six, establish the plate lattice structure reinforced composite material model

[0065] (1) In the three-dimensional modeling software, a cube model BIGCUBIC with a side length of 2L is established, and the eight vertices of the cube model BIGCUBIC are (-L, -L, -L), (-L, -L, L), (-L, L, L), (-L, L, -L), (L, -L, -L), (L, -L, L), (L, L, L), (L, L, -L).

[0066] (2) The second plate lattice structure model BIGUNIT obtained in step five is subtracted from the cube model BIGCUBIC to obtain the matrix material model.

[0067] (3) The matrix material model is subtracted from the cube model BIGCUBIC to obtain the reinforcing material model.

[0068] (4) The plate lattice structure reinforced composite material model is obtained by assembling the matrix material model and the reinforcing material model.

[0069] The first plate lattice structure model UNIT is established. Since the triangular surface is thickened into a plate, it is possible that the plate lattice does not completely penetrate the CUBIC cube space, that is, the positive normal thickening, the edge and corner of the plate protrude outside the CUBIC cube, while the negative normal thickening, the edge and corner of the plate are still inside the CUBIC cube and do not penetrate the CUBIC cube, causing a geometric error. This error is only near the inner surface of the CUBIC cube. Since the second plate lattice structure model BIGUNIT is stacked in the X, Y, Z directions from the first plate lattice structure model UNIT, the center cube space with a side length of 2L is located inside the model, and no geometric error is generated.

[0070] Seven, finite element numerical simulation calculation

[0071] (1) The plate lattice structure reinforced composite material model is meshed, and the mesh type in the meshing is 4-node tetrahedral element, and the total number of mesh elements is not less than 500,000.

[0072] (2) The plate lattice structure reinforced composite material model after meshing is subjected to tensile boundary conditions:

[0073] The value range of the maximum tensile strain E is set to 0.1% to 10%; the value range of the tensile rate S is set to 0.0001s -1 ~ 0.01s -1 ;

[0074] If the stretching direction is the X direction, the X direction displacement of all the grid nodes in the X = -L plane is constrained to be 0, and the X direction displacement of all the grid nodes in the X = L plane is applied, and the displacement amount is 2L x E;

[0075] If the stretching direction is the Y direction, the Y direction displacement of all the grid nodes in the Y = -L plane is constrained to be 0, and the Y direction displacement of all the grid nodes in the Y = L plane is applied, and the displacement amount is 2L x E;

[0076] If the stretching direction is the Z direction, the Z direction displacement of all the grid nodes in the Z = -L plane is constrained to be 0, and the Z direction displacement of all the grid nodes in the Z = L plane is applied, and the displacement amount is 2L x E.

[0077] (3) The material properties (including Young's modulus, Poisson's ratio, yield strength, stress-strain curve of plastic deformation section) of the matrix material and the reinforcing material are input respectively, the mechanical behavior of the plate lattice structure reinforced composite material during the stretching process is simulated, and the Young's modulus, Poisson's ratio, strength and elongation of the plate lattice structure composite material are obtained.

[0078] ABAQUS, ANSYS or Comsol finite element software can be used for numerical simulation.

[0079] Example 1

[0080] The embodiment provides a mechanical behavior prediction method of a plate lattice reinforced composite material, and the specific steps are as follows:

[0081] I. Create a cube model CUBIC with an edge length of 50 in a three-dimensional modeling software, and the eight vertices are (0, 0, 0), (0, 0, 50), (0, 50, 50), (0, 50, 0), (50, 0, 0), (50, 0, 50), (50, 50, 50), (50, 50, 0).

[0082] II. In the three-dimensional modeling software, select a triangular plate, input the plate number N = 3 of the plate model; determine the plate thickness T = 2.5.

[0083] The vertex coordinates of the three triangular plates are respectively: the first plate P11 (0, 0, 0), P21 (50, 50, 50), P31 (50, 0, 0), the second plate P12 (0, 0, 0), P22 (50, 50, 50), P23 (0, 50, 0), and the third plate P13 (0, 0, 0), P23 (50, 50, 50), P33 (0, 0, 50). The established triangular plate model is as shown in Figure 1 .

[0084] III. Make each triangular plate along its positive and negative normal respectively thickened by 1.25, to obtain a 1 / 8 plate series lattice unit model, as shown in Figure 2 .

[0085] IV. Mirror the obtained 1 / 8 plate series lattice unit model in the XOY plane, then merge and mirror in the YOZ plane, then merge and mirror in the ZOX plane, to obtain a first plate series lattice structure model UNIT, as shown in Figure 3 .

[0086] V. Copy 7 copies of the first plate series lattice structure model, and move them along the vectors (0, 0, -2L), (0, -2L, -2L), (0, -2L, 0), (-2L, 0, 0), (-2L, 0, -2L), (-2L, -2L, -2L), (-2L, -2L, 0) respectively. Merge the first plate series lattice structure model UNIT and the moved models to obtain a second plate series lattice structure model BIGUNIT, as shown in Figure 4 .

[0087] VI. Establish a cubic model BIGCUBIC with a side length of 2L, and its 8 vertices are (-L, -L, -L), (-L, -L, L), (-L, L, L), (-L, L, -L), (L, -L, -L), (L, -L, L), (L, L, L), (L, L, -L).

[0088] Subtract the second plate series lattice structure model BIGUNIT from the cubic model BIGCUBIC to obtain a matrix material model MATRIX, as shown in Figure 5 .

[0089] Subtract the matrix material model MATRIX from the cubic model BIGCUBIC to obtain a reinforcement material model REINFORCEMENT, as shown in Figure 6 .

[0090] Assemble the matrix material model MATRIX and the reinforcement material model REINFORCEMENT to obtain a plate series lattice structure reinforced composite material model COMPOSITE, as shown in Figure 7 .

[0091] VII. Mesh the plate series lattice structure reinforced composite material model COMPOSITE, and the mesh type in the meshing is a 4-node tetrahedral element, and the total number of mesh elements is not less than 500,000.

[0092] VIII. Input material properties and apply boundary conditions to the plate series lattice structure reinforced composite material model COMPOSITE, and use finite element software to calculate the mechanical behavior under load conditions.

[0093] (1) Using commercial finite element software ABAQUS, input material properties, the matrix material is 6061 aluminum (Al, Young's modulus 69 GPa, Poisson's ratio 0.33), and the reinforcing material is silicon carbide (SiC, Young's modulus 427 GPa, Poisson's ratio 0.15). The yield strength of 6061 aluminum is 267 MPa, and the stress-strain relationship is as shown in Figure 8 . The silicon carbide is a pure elastic material without yield strength and plastic deformation.

[0094] (2) Tensile strain E = 1%, strain rate S = 0.0001 s -1 .

[0095] (3) Numerical simulation of the mechanical behavior of the lattice structure reinforced composite material under tensile load conditions, and obtain the stress distribution of the lattice structure reinforced composite material Figure 9 ) and mechanical properties Figure 10 ).

[0096] This embodiment establishes a lattice structure reinforced composite material model. The lattice structure is relatively complex. Figure 9 The stress distribution of the matrix and the reinforcing material. It can be found that the stress distribution of the composite material is well predicted. In the aluminum matrix near the silicon carbide lattice structure, there is a certain gradient distribution, and the stress level of the matrix is higher near the reinforcing phase. However, its stress level (133-400 MPa) is much lower than that of the silicon carbide reinforcing material (800-1600 MPa). The stress level in the reinforcing material is also not uniformly distributed. From the overall graph and each cross-sectional graph, it can be seen that the stress level of the reinforcing material along the X direction (tensile direction) is the highest, and the stress of the silicon carbide plate plane decreases with the increase of the orientation angle. It can be seen that the method provided by the present application can effectively predict the mechanical behavior of the lattice structure reinforced composite material with complex structure.

[0097] The above-described embodiments are only a preferred scheme of the present application, and are not intended to limit the present application. Those skilled in the art can make various changes and modifications without departing from the spirit and scope of the present application. Therefore, any technical solution obtained by equivalent replacement or equivalent transformation falls within the protection scope of the present application.

Claims

1. A method for predicting the mechanical behavior of a ply-based lattice reinforced composite material, characterized in that, The specific steps are as follows: S1: creating a cubic model CUBIC with edge length L in a three-dimensional modeling software; S2: establishing a triangular plate model in the three-dimensional modeling software based on the number N of plates; S3: thickening each triangular plate in the triangular plate model to obtain a 1 / 8 plate lattice unit model; S4: performing mirror symmetry on the 1 / 8 plate lattice unit model obtained in step S3 in the XOY plane of the Cartesian coordinate system, combining, then performing mirror symmetry on the combined model in the YOZ plane, combining again, and then performing mirror symmetry on the combined model in the ZOX plane to obtain a first plate lattice structure model; S5: doubling the first plate lattice structure model obtained in step S4 along the X, Y and Z axes of the Cartesian coordinate system to obtain a second plate lattice structure model; S6: establishing a cubic model BIGCUBIC with edge length 2L; performing body subtraction in the modeling software to subtract the second plate lattice structure model from the cubic model BIGCUBIC to obtain a matrix material model; subtracting the matrix material model from the cubic model BIGCUBIC to obtain a reinforcing body material model; S6: assembling the matrix material model and the reinforcing body material model to obtain a plate lattice structure reinforced composite material model; S7: performing grid division on the plate lattice structure reinforced composite material model and applying tensile boundary conditions; Inputting the material properties of the matrix material and the reinforcing body material respectively, the mechanical behavior of the plate lattice structure reinforced composite material in the tensile process is numerically simulated to obtain the Young's modulus, Poisson's ratio, strength and elongation of the plate lattice structure composite material.

2. The method of predicting the mechanical behavior of a lattice-reinforced composite material of a panel according to claim 1, characterized in that, The three-dimensional modeling software includes AutoCAD, Blender, Rhino, Abaqus or Ansys software.

3. The method of predicting the mechanical behavior of a lattice-reinforced composite material of a panel according to claim 1, characterized in that, The 8 vertices of the cubic model CUBIC are (0, 0, 0), (0, 0, L), (0, L, L), (0, L, 0), (L, 0, 0), (L, 0, L), (L, L, L) and (L, L, 0); and the 8 vertices of the cubic model BIGCUBIC are (-L, -L, -L), (-L, -L, L), (-L, L, L), (-L, L, -L), (L, -L, -L), (L, -L, L), (L, L, L) and (L, L, -L).

4. The method of predicting the mechanical behavior of a lattice-reinforced composite material of a panel according to claim 1, characterized in that, The triangular plate model establishing method in step S2 is as follows: S201: inputting three vertex coordinates so that they are all located on the surface of the cubic model CUBIC, and determining a triangular plate according to the three vertices; S202: based on the number N of plates, repeating step S201 N times to determine N triangular plates; and combining the N triangular plates to obtain a triangular plate model.

5. The method of predicting the mechanical behavior of a lattice-reinforced composite material of a panel according to claim 1, characterized in that, In step S3, each triangular plate is thickened by T / 2 along its positive and negative normal directions respectively, so that the plate thickness is T, and a 1 / 8 plate lattice unit model is obtained.

6. The method of predicting the mechanical behavior of a lattice-reinforced composite material of a panel according to claim 1, characterized in that, Step S4 is as follows: S401: Copy a copy of the 1 / 8 plate series lattice unit model, mirror symmetry in the XOY plane of the Cartesian coordinate system, get 1 / 8 plate series lattice unit symmetry model; after merging the 1 / 8 plate series lattice unit model and the 1 / 8 plate series lattice unit symmetry model, get 1 / 4 plate series lattice unit model; S402: Copy a copy of the 1 / 4 plate series lattice unit model, mirror symmetry in the YOZ plane of the Cartesian coordinate system, get 1 / 4 plate series lattice unit symmetry model; After merging the 1 / 4 plate series lattice unit model and the 1 / 4 plate series lattice unit symmetry model, get 1 / 2 plate series lattice unit model; S403: Copy a copy of the 1 / 2 plate series lattice unit model, mirror symmetry in the ZOX plane of the Cartesian coordinate system, get 1 / 2 plate series lattice unit symmetry model; after merging the 1 / 2 plate series lattice unit model and the 1 / 2 plate series lattice unit symmetry model, get the first plate series lattice structure model.

7. The method of predicting the mechanical behavior of a lattice-reinforced composite material of a panel according to claim 1, characterized in that, Step S5 is specifically as follows: S501: Copy 7 copies of the first plate series lattice structure model, respectively along the vector (0, 0, -2L), (0, -2L, -2L), (0, -2L, 0), (-2L, 0, 0), (-2L, 0, -2L), (-2L, -2L, -2L), (-2L, -2L, 0) move; S502: After merging the first plate series lattice structure model and the model moved in step S501, get the second plate series lattice structure model.

8. The method of predicting the mechanical behavior of a lattice-reinforced composite material of a panel according to claim 1, characterized in that, In step S7, the grid type in the grid division is a 4-node tetrahedral element, and the total number of grid elements is not less than 500000.

9. The method of predicting the mechanical behavior of a lattice-reinforced composite material of a panel according to claim 1, characterized in that, In step S7, the stretching boundary condition is set as follows: S701: set the value range of the maximum tensile strain E to be 0.1%~10%; set the value range of the tensile rate S to be 0.0001s -1 ~0.01s -1 ; S702: If the stretching direction is X direction, the X direction displacement of all grid nodes on the X=-L plane is constrained to be 0, and the X direction displacement of all grid nodes on the X=L plane is applied, the displacement amount is 2L×E; if the stretching direction is Y direction, the Y direction displacement of all grid nodes on the Y=-L plane is constrained to be 0, and the Y direction displacement of all grid nodes on the Y=L plane is applied, the displacement amount is 2L×E; if the stretching direction is Z direction, the Z direction displacement of all grid nodes on the Z=-L plane is constrained to be 0, and the Z direction displacement of all grid nodes on the Z=L plane is applied, the displacement amount is 2L×E.

10. The method of predicting the mechanical behavior of a lattice-reinforced composite material of a panel according to claim 1, characterized in that, In step S7, ABAQUS, ANSYS or Comsol finite element software is used for numerical simulation.

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