Progressive damage analysis method of composite material one-way plate based on ABAQUS

Abstract

The invention belongs to the field of finite element simulation of fiber reinforced composites, and provides a finite element simulation method for progressive damage analysis of a composite one-way plate, which comprises the following steps of: S1, writing a VUMAT subprogram by adopting an FORTRAN language based on a three-dimensional Hashin failure criterion, and realizing numerical simulation of stretching of the composite one-way plate based on the three-dimensional Hashin failure criterion; and S2, a progressive damage analysis model of the composite material one-way plate is established through finite element software ABAQUS, and initial damage judgment and rigidity degradation analysis of the composite material one-way plate in the stretching process are achieved. According to the method, the VUMAT subprogram of the ABAQUS is utilized to realize initial damage judgment and rigidity degradation analysis of the composite material one-way plate in the stretching process, so that the blank in the field of progressive damage and rigidity degradation analysis of the composite material one-way plate under the condition of bearing the tensile load is filled up, and a necessary theory is provided for the important field; and theoretical support is provided for selection and application of materials.

Description

Technical Field

[0001] The invention belongs to the field of finite element simulation of fiber reinforced composite materials, and in particular relates to a finite element simulation method for progressive damage analysis of a composite unidirectional plate. Background Art

[0002] Carbon fiber has the characteristics of light weight, high strength, high modulus, stable chemical properties, etc. Carbon fiber reinforced composite materials have attracted wide attention in the fields of aerospace and structural reinforcement due to their high specific strength, high specific stiffness, good fatigue resistance and corrosion resistance, and easy processing. Unidirectional carbon fiber composite panels are widely used in the field of building reinforcement due to their excellent axial mechanical properties.

[0003] Unidirectional fiber reinforced composite panels are orthotropic composite materials. Due to the directional arrangement of fibers, there are significant differences in the mechanical properties of unidirectional panels in the fiber direction and perpendicular to the fiber direction. The tensile strength and modulus in the fiber direction are much higher than those perpendicular to the fiber direction. The compressive strength of unidirectional panels in the fiber direction is also lower than the tensile strength. When subjected to load, the failure mode of unidirectional panels may include fiber breakage, matrix cracking, and debonding of the fiber-matrix interface. Due to its anisotropic properties, the relationship between the load direction and material properties must be fully considered during design to ensure the stability and safety of the structure. In many scenarios, out-of-plane impact or shear force of composite unidirectional panels must be considered, and out-of-plane failure occurs. The two-dimensional Hashin failure criterion in ABAQUS cannot be used to determine this. The three-dimensional Hashin failure criterion must be used to determine whether the material is damaged. Therefore, it is necessary to write a VUMAT subroutine to implement numerical simulation based on the three-dimensional Hashin failure criterion.

[0004] Patent "CN117828936A" discloses a finite element simulation method for progressive damage analysis of composite bolt connections. It uses the VUMAT subroutine to realize secondary development of ABAQUS software and performs three-dimensional progressive damage analysis on composite bolt connection structures. Although the patent mentions a damage model based on the Hashin failure criterion, it does not cover in-plane or out-of-plane damage modes of the model, such as in-plane shear failure, out-of-plane shear failure, etc. Summary of the invention

[0005] In order to solve the above problems, the present invention proposes a finite element simulation method for progressive damage analysis of a composite one-way plate.

[0006] The technical solution adopted by the present invention is as follows:

[0007] The present invention proposes a finite element simulation method for progressive damage analysis of composite one-way plates. The steps are as follows:

[0008] Step S1: Based on the three-dimensional Hashin failure criterion, a VUMAT subroutine is written using FORTRAN language to realize the numerical simulation of the unidirectional tensile stress of the composite material based on the three-dimensional Hashin failure criterion;

[0009] Step S2: The finite element software ABAQUS is used to establish a progressive damage analysis model for the composite one-way plate, so as to realize the initial damage determination and stiffness degradation analysis of the composite one-way plate during the tensile process.

[0010] Preferably, step S1 comprises:

[0011] Step S11: Write material properties according to the user material set in ABAQUS;

[0012] Step S12: input the damage stiffness matrix, the three-dimensional Hashin failure criterion and the stiffness degradation code;

[0013] Step S13: Save and create a subroutine file that complies with the VUMAT specification for use in ABAQUS finite element analysis software.

[0014] Preferably, according to the user material set in ABAQUS, the written material properties include: Young's modulus E11 in the X-axis direction, Young's modulus E22 in the Y-axis direction, Young's modulus E33 in the Z-axis direction, shear modulus G12 in the XY plane, shear modulus G13 in the XZ plane, shear modulus G23 in the YZ plane, Poisson's ratio v12 in the XY plane, Poisson's ratio v13 in the XZ plane, Poisson's ratio v23 in the YZ plane, tensile strength Xt in the X-axis direction, compressive strength Xc in the X-axis direction, tensile strength Yt in the Y-axis direction, compressive strength Yc in the Y-axis direction, tensile strength Zt in the Z-axis direction, compressive strength Zc in the Z-axis direction, shear strength S12 in the XY plane, shear strength S13 in the XZ plane, shear strength S23 in the YZ plane; wherein 1, 2, and 3 represent the fiber direction (X), the in-plane vertical direction (Y), and the out-of-plane vertical direction (Z), respectively.

[0015] Preferably, the present invention takes carbon fiber composite material unidirectional plate as the research object.

[0016] Preferably, step S2 comprises:

[0017] Step S21: Modeling the composite one-way plate structure using finite element analysis software ABAQUS.

[0018] Step S22: define material cross-section properties, input the material properties of the composite unidirectional plate into the user material; define the fiber direction of the composite laminate, and use solid elements;

[0019] Step S23: setting explicit dynamic analysis steps and setting the total duration;

[0020] Step S24: defining boundary conditions: a completely fixed constraint is set at one end of the composite one-way plate, i.e., the six degrees of freedom U1, U2, U3, UR1, UR2, and UR3 are all 0, and a load is applied to the other end;

[0021] Step S25: Divide the model into hexahedral meshes in the Mesh module, all using the C3D8R mesh type;

[0022] Through the above steps, the three-dimensional progressive damage analysis model of composite one-way plates was established;

[0023] Step S26: In the job interface of ABAQUS, add the VUMAT subroutine, associate the VUMAT subroutine with the model processed by step S25, and call the VUMAT subroutine for the Hashin failure criterion to solve and analyze.

[0024] The invention has the following beneficial effects:

[0025] The present invention provides a finite element simulation method for progressive damage analysis of a composite one-way plate. The VUMAT subroutine of ABAQUS is used to realize the numerical simulation of the Hashin failure criterion. The initial damage judgment and stiffness degradation analysis of the composite one-way plate during the stretching process are realized in ABAQUS, and the initial damage generated in the composite one-way plate during the stretching process can be effectively analyzed. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 It is a schematic diagram of a composite one-way plate model;

[0027] Figure 2 Schematic diagram to define the fiber direction of unidirectional composite plate;

[0028] Figure 3 Schematic diagram for defining the boundary conditions of a composite one-way plate;

[0029] Figure 4 Schematic diagram of mesh division for one-way composite plate.

[0030] Figure 5 This is a cloud diagram of the simulation results of the axial stress distribution state of the composite one-way plate.

[0031] Figure 6 This is the progressive damage contour of the composite one-way plate. DETAILED DESCRIPTION

[0032] In order to make the purpose, technical solution and advantages of the present invention more clearly understood, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not used to limit the present invention.

[0033] The specific implementation of the present invention is described in detail below in conjunction with specific embodiments.

[0034] An embodiment of the present invention relates to a finite element simulation method for progressive damage analysis of a composite material one-way plate, comprising the following steps:

[0035] Step S1: Based on the three-dimensional Hashin failure criterion, a VUMAT subroutine is written using FORTRAN language to realize the numerical simulation of the unidirectional tensile stress of the composite material based on the three-dimensional Hashin failure criterion;

[0036] Step S2: The progressive damage analysis model of the composite one-way plate is established by using the finite element software ABAQUS to realize the initial damage judgment and stiffness degradation analysis of the composite one-way plate during the tensile process.

[0037] Preferably, step S1 comprises:

[0038] Step S11: Write material properties according to the user material set in ABAQUS;

[0039] The material properties include: Young's modulus E11 in the X-axis direction, Young's modulus E22 in the Y-axis direction, Young's modulus E33 in the Z-axis direction, shear modulus G12 in the XY plane, shear modulus G13 in the XZ plane, shear modulus G23 in the YZ plane, Poisson's ratio ν12 in the XY plane, Poisson's ratio v13 in the XZ plane, Poisson's ratio v23 in the YZ plane, tensile strength Xt in the X-axis direction, compressive strength Xc in the X-axis direction, tensile strength Yt in the Y-axis direction, compressive strength Yc in the Y-axis direction, tensile strength Zt in the Z-axis direction, compressive strength Zc in the Z-axis direction, shear strength S12 in the XY plane, shear strength S13 in the XZ plane, shear strength S23 in the YZ plane; among which, 1, 2, and 3 represent the fiber direction (X), the in-plane perpendicular direction (Y), and the out-of-plane perpendicular direction (Z), respectively.

[0040] Step S12: input the damage stiffness matrix, the three-dimensional Hashin failure criterion and the stiffness degradation code;

[0041] The stiffness matrix is ​​as follows:

[0042]

[0043] Among them, σ ij (i,j=1,2,3) is the stress component, ε ij(i,j=1,2,3) is the strain component, Eii(i=1,2,3) is the tensile modulus, Gij(i,j=1,2,3,i≠j) is the shear modulus, v ij (i, j = 1, 2, 3, i ≠ j) is the Poisson’s ratio, and 1, 2, and 3 represent the fiber direction, the in-plane perpendicular direction, and the out-of-plane perpendicular direction, respectively.

[0044] Γ is defined as follows:

[0045] Γ=1(1-v 12 v 21 -v 23 v 32 -v 13 v 31 -2v 21 v 32 v 13 )

[0046] Moreover, Poisson's ratio and elastic modulus satisfy the following formula:

[0047]

[0048] The Hashin failure criteria are as follows:

[0049] Fiber tensile failure mode (ε 11 ≥0):

[0050]

[0051] Fiber compression failure mode (ε 11 <0):

[0052]

[0053] Matrix tensile failure mode (ε 22 +ε 33 ≥0):

[0054]

[0055] Matrix compression failure mode (ε 22 +ε 33 <0):

[0056]

[0057] In-plane shear failure mode (1-2 plane):

[0058]

[0059] Out-of-plane shear failure mode (1-3 and 2-3 planes):

[0060]

[0061] Among them, 1, 2, and 3 represent the fiber direction (X), the in-plane perpendicular direction (Y), and the out-of-plane perpendicular direction (Z), respectively. 11T and ε 11C is the tensile and compressive failure strain in the fiber direction, ε 22T and ε 22C are the tensile and compressive failure strains in the matrix direction, ε ijf (i,j=1,2,3,i≠j) is the shear failure strain. A composite material layer can have multiple damage modes at the same time. When any damage parameter (f ft ,f fc ,f mt ,f mc ,f ip ,f op ) reaches 1, the unit meets the corresponding damage initiation criterion, and then stiffness degradation occurs, and the material stiffness is defined to drop sharply to 5% of the original value.

[0062] Step S13: Save and create a subroutine file that complies with the VUMAT specification for use in ABAQUS finite element analysis software.

[0063] Step S2 includes:

[0064] Step S21: Use finite element analysis software ABAQUS to model the composite one-way plate structure, such as Figure 1 As shown;

[0065] Step S22: define the material section properties, input the composite material one-way plate material properties into the user material; define the fiber direction of the composite material one-way plate, and use solid elements, such as Figure 2 As shown;

[0066] Step S23: Set the explicit dynamic analysis step and set the total duration to 1 second.

[0067] Step S24: Define boundary conditions: A completely fixed constraint is set at one end of the composite unidirectional plate, i.e., all six degrees of freedom U1, U2, U3, UR1, UR2, and UR3 are 0, and a load is applied to the other end, such as Figure 3 shown.

[0068] Step S25: In the Mesh module, the model is divided into hexahedral meshes, all using the C3D8R mesh type, such as Figure 4 Through the above steps, the three-dimensional progressive damage analysis model of composite one-way plates is established;

[0069] Step S26: In the job interface of Abaqsus, add the VUMAT subroutine, associate the VUMAT subroutine with the model processed by step S25, and call the VUMAT subroutine for the Hashin failure criterion to solve and analyze.

[0070] The simulation result cloud diagram of the stress distribution state of the composite one-way plate obtained after simulation analysis is as follows Figure 5 As shown, the progressive damage cloud diagram is as follows Figure 6 shown.

[0071] The preferred embodiments of the present invention are described in detail above in conjunction with the accompanying drawings. It should be pointed out that the protection scope of the present invention is not limited to the specific details in the above embodiments. For those skilled in the art, they can still modify the technical solutions recorded in the aforementioned examples, or make equivalent substitutions for some of the technical features therein. However, any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A finite element simulation method for progressive damage analysis of composite one-way plates, characterized by: The following steps are involved: Step S1: Based on the three-dimensional Hashin failure criterion, a VUMAT subroutine is written in FORTRAN language to realize the numerical simulation of the unidirectional tensile stress of the composite material based on the three-dimensional Hashin failure criterion; Step S2: The progressive damage analysis model of the composite one-way plate is established by using the finite element software ABAQUS to realize the initial damage judgment and stiffness degradation analysis of the composite one-way plate during the tensile process.

2. The finite element simulation method for progressive damage analysis of composite one-way plates according to claim 1, characterized in that: Step S1 includes: Step S11: Write material properties according to the user material set in ABAQUS; Step S12: input the damage stiffness matrix, the three-dimensional Hashin failure criterion and the stiffness degradation code; Step S13: Save and create a subroutine file that complies with the VUMAT specification for use in ABAQUS finite element analysis software.

3. The finite element simulation method for progressive damage analysis of composite one-way plates according to claim 1, characterized in that: Step S2 includes: Step S21: Modeling the composite one-way plate structure using finite element analysis software ABAQUS in the Part module; Step S22: define the material section properties in the Property module, input the material properties of the composite unidirectional plate into the user material; define the fiber direction of the composite laminate, and use solid elements; Step S23: set the explicit dynamic analysis step in the Step module and set the total duration; Step S24: define boundary conditions: in the Load module, set a completely fixed constraint on one end of the composite one-way plate, that is, all six degrees of freedom U1, U2, U3, UR1, UR2, and UR3 are 0, and apply a load on the other end; Step S25: Divide the model into hexahedral meshes in the Mesh module, using the C3D8R mesh type; Through the above steps, the progressive damage analysis model of composite one-way plates was established; Step S26: In the Job interface of ABAQUS, add the VUMAT subroutine, associate the VUMAT subroutine with the model processed by step S25, and call the VUMAT subroutine for the Hashin failure criterion to solve and analyze.

4. The finite element simulation method for progressive damage analysis of composite one-way plates according to claim 1, characterized in that: The VUMAT subroutines are written to be strain based.

5. The finite element simulation method for progressive damage analysis of composite one-way plates according to claim 1, characterized in that: When the composite one-way plate meets the initial damage condition, the stiffness drops sharply to 5%.

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