CN116796577A - Reverse multi-scale method for representing composite material fiber-matrix interface damage - Google Patents
Reverse multi-scale method for representing composite material fiber-matrix interface damage Download PDFInfo
- Publication number
- CN116796577A CN116796577A CN202311078382.5A CN202311078382A CN116796577A CN 116796577 A CN116796577 A CN 116796577A CN 202311078382 A CN202311078382 A CN 202311078382A CN 116796577 A CN116796577 A CN 116796577A
- Authority
- CN
- China
- Prior art keywords
- strength
- fiber
- composite material
- matrix
- stress
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 239000002131 composite material Substances 0.000 title claims abstract description 70
- 239000011159 matrix material Substances 0.000 title claims abstract description 45
- 238000000034 method Methods 0.000 title claims abstract description 45
- 230000006378 damage Effects 0.000 title claims abstract description 29
- 239000000835 fiber Substances 0.000 claims abstract description 41
- 239000000463 material Substances 0.000 claims abstract description 31
- 238000006073 displacement reaction Methods 0.000 claims abstract description 12
- 230000000737 periodic effect Effects 0.000 claims abstract description 12
- 230000006835 compression Effects 0.000 claims description 15
- 238000007906 compression Methods 0.000 claims description 15
- 238000004364 calculation method Methods 0.000 claims description 7
- 238000004422 calculation algorithm Methods 0.000 claims description 4
- 230000008569 process Effects 0.000 claims description 4
- 241001274658 Modulus modulus Species 0.000 claims description 3
- 125000003275 alpha amino acid group Chemical group 0.000 claims description 3
- 150000001875 compounds Chemical class 0.000 claims description 3
- 230000002706 hydrostatic effect Effects 0.000 claims description 3
- 238000012821 model calculation Methods 0.000 claims description 3
- 239000004033 plastic Substances 0.000 claims description 3
- 239000010410 layer Substances 0.000 description 13
- 229920000049 Carbon (fiber) Polymers 0.000 description 7
- 239000004917 carbon fiber Substances 0.000 description 7
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 6
- 238000011160 research Methods 0.000 description 3
- 238000007789 sealing Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 239000011148 porous material Substances 0.000 description 2
- 239000004593 Epoxy Substances 0.000 description 1
- 238000004458 analytical method Methods 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 238000012512 characterization method Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000003733 fiber-reinforced composite Substances 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 239000011229 interlayer Substances 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000005192 partition Methods 0.000 description 1
- 239000002356 single layer Substances 0.000 description 1
Classifications
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
-
- G—PHYSICS
- G16—INFORMATION AND COMMUNICATION TECHNOLOGY [ICT] SPECIALLY ADAPTED FOR SPECIFIC APPLICATION FIELDS
- G16C—COMPUTATIONAL CHEMISTRY; CHEMOINFORMATICS; COMPUTATIONAL MATERIALS SCIENCE
- G16C20/00—Chemoinformatics, i.e. ICT specially adapted for the handling of physicochemical or structural data of chemical particles, elements, compounds or mixtures
- G16C20/40—Searching chemical structures or physicochemical data
-
- G—PHYSICS
- G16—INFORMATION AND COMMUNICATION TECHNOLOGY [ICT] SPECIALLY ADAPTED FOR SPECIFIC APPLICATION FIELDS
- G16C—COMPUTATIONAL CHEMISTRY; CHEMOINFORMATICS; COMPUTATIONAL MATERIALS SCIENCE
- G16C60/00—Computational materials science, i.e. ICT specially adapted for investigating the physical or chemical properties of materials or phenomena associated with their design, synthesis, processing, characterisation or utilisation
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2113/00—Details relating to the application field
- G06F2113/26—Composites
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces
Landscapes
- Engineering & Computer Science (AREA)
- Theoretical Computer Science (AREA)
- Computing Systems (AREA)
- Life Sciences & Earth Sciences (AREA)
- Crystallography & Structural Chemistry (AREA)
- Physics & Mathematics (AREA)
- Chemical & Material Sciences (AREA)
- Bioinformatics & Computational Biology (AREA)
- Bioinformatics & Cheminformatics (AREA)
- Evolutionary Computation (AREA)
- General Physics & Mathematics (AREA)
- General Engineering & Computer Science (AREA)
- Geometry (AREA)
- Computer Hardware Design (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
The invention discloses a reverse multi-scale method for representing composite material fiber-matrix interface damage, and relates to the technical field of composite material multi-scale computational mechanics. Selecting a macroscopic structure of the composite material, and determining the volume fraction of the fiberThe engineering elastic constant and the strength of each direction of the material; applying load to the macro structure of the composite material, judging the failure condition of the weak area, and extracting the strain component of the weak area; on the mesostructure, RVE generation is based on random fiber distributionAlgorithm, generating fiber volume fraction asThe random distribution RVE of the fibers, and the parameters of the fiber structure and the material and the parameters of the matrix structure and the material are determined; applying periodic boundary conditions to the random distribution RVE of the fibers to ensure the continuity of the stress and displacement of the microstructure; and applying the strain component of the extracted composite material macrostructure weak area to the fiber random distribution RVE, and calculating and characterizing the damage condition of the RVE fiber-matrix interface of the composite material.
Description
Technical Field
The invention relates to the technical field of multi-scale computational mechanics of composite materials, in particular to a reverse multi-scale method for representing the damage of a fiber-matrix interface of a composite material.
Background
The composite material (mainly referred to as fiber reinforced composite material) has been popular in the fields of aerospace, industrial manufacturing, medical equipment, sports equipment, building structures and the like because of incomparable advantages such as light structural weight, strong designability, good mechanical properties and the like, and has been widely applied. Nevertheless, there are a number of challenges in using composite materials. Because of the factors of great anisotropy of carbon fibers, great difference between the fibers and the fundamental structural characteristics of the matrix, initial defects of the fiber-matrix interface, incomplete interlayer strength theory and the like, the method brings great challenges to research analysis and design production of the composite material. At present, the research of a carbon fiber reinforced phase is expanded to a nano scale, and how to predict the macroscopic performance of a composite material through the intrinsic performance of components on microscopic and microscopic scales is a problem which is difficult to solve by classical laminate theory and continuous medium mechanics. On the other hand, when the macrostructures are loaded, their structural failure is often analyzed by classical composite failure theory (e.g., tsai-Hill criterion, tsai-Wu criterion), but its composition (fiber-matrix interface) may already be damaged when the macroscopically manifestation is not damaged. This is important to investigate the safety of structures such as composite unlined V-type pressure vessels. With the continuous development of computer computing power, a multiscale method based on a finite element method can better establish the connection between the microscopic characteristics and macroscopic performance in the field of composite material mechanics, and is one of main means for evaluating the mechanical properties in the field of composite materials.
In the multiscale approach, a representative volume element (Representative volume element, RVE) describing the microstructure of the composite is a key model of the multiscale mechanics of the composite. The RVE applying the periodic boundary condition is loaded, so that the macroscopic engineering elastic constant and the strength of the composite material are predicted, and the method is a main research content of multi-scale calculation of the composite material at present. In this process, damage and destruction always starts at the fiber-matrix interface region, which becomes the weakest point of the composite. However, when the macrostructure damage of the composite material is calculated, classical composite material failure theories (such as Tsai-Hill criterion and Tsai-Wu criterion) are mainly adopted, and the macrostructure failure theories can only represent fiber damage and matrix damage, but cannot represent damage and damage states of a fiber-matrix interface. Therefore, it is of great importance to develop a method that is capable of characterizing the disruption of the fiber-matrix interface.
Disclosure of Invention
The invention aims to provide a reverse multi-scale method for representing the damage of a composite material fiber-matrix interface, which is a macroscopic-microscopic multi-scale damage representation method developed for the field of multi-scale computational mechanics of composite materials and has important significance for predicting the sealing failure of a composite material pressure vessel based on microscopic scale.
To achieve the above object, the present invention provides a reverse multiscale method of characterizing composite fiber-matrix interfacial failure, comprising the steps of:
s1, selecting a macroscopic structure of a composite material, and determining the volume fraction of fibersThe engineering elastic constant and the strength of each direction of the material;
s2, applying load to the composite material macrostructure in the step S1, determining a weak area, judging the failure condition of the weak area, and extracting the strain component of the weak area of the composite material macrostructure by checking the strain component of the integral point of the failure unit;
s3, generating according to a fiber random distribution RVE generation algorithm on a mesoscopic structureThe fiber forming volume fraction isThe random distribution RVE of the fibers, and determining the fiber structure and material parameters, the matrix structure and material parameters;
s4, applying periodic boundary conditions to the random distribution RVE of the fibers to ensure the continuity of the stress and displacement of the microstructure;
s5, applying the strain component of the macrostructure weak area of the composite material extracted in the step S2 to the random fiber distribution RVE of the periodic boundary condition applied in the step S4, and calculating and representing the damage condition of the RVE fiber-matrix interface of the composite material.
Preferably, in step S1, the engineering elastic constants of the material include elastic modulus, shear modulus and poisson ratio; the elastic modulus includes 1-direction elastic modulusModulus of elasticity in 2 direction>3 modulus of elasticity>The method comprises the steps of carrying out a first treatment on the surface of the The shear modulus includes 1-2 direction shear modulus +.>1-3 shear modulus +.>2-3 shear modulus +.>The method comprises the steps of carrying out a first treatment on the surface of the Poisson ratio includes 1-2 directional Poisson ratioPoisson's ratio in 1-3 direction>Poisson's ratio in 2-3 direction->；
The hoop strength includes tensile strength, compressive strength, and shear strength; tensile strength includes 1-direction tensile strength2-direction tensile Strength->The method comprises the steps of carrying out a first treatment on the surface of the The compressive strength includes 1-direction compressive strength->2-way compression Strength->The method comprises the steps of carrying out a first treatment on the surface of the The shear strength includes 1-2 directional shear strength +.>1-3 shear Strength->And 2-3 direction shear Strength +.>。
Preferably, in step S2, the stress is determined by a maximum stress criterion,Criterion, & gt>The criterion judges the failure condition of the weak area, and is specifically as follows:
（1）
in the formula (1), the components are as follows,is the tensile/compressive strength of the unidirectional sheet 1 in the direction, wherein the tensile strength is +.>Compression is +.>；/>For the unidirectional sheet 2 direction stretching/compression strength, stretching is +.>Compression is +.>；/>Stress in 1 direction>Stress in 2 directions>Stress in the direction of 1-2; />As a failure factor, ++>I.e., composite failure;
the criterion calculation formula is as follows:
（2）
the criterion calculation formula is as follows:
（3）
in the formula (3), the coefficients are defined as follows:
（4）。
preferably, in step S3, the fiber is basically a transverse isotropic material, and the material parameter is engineering elastic constant 、/> 、/> 、/> 、/>And->；
The matrix is basically made of isotropic elastoplastic material, and the material parameters comprise engineering elastic constants 、/> 、/>And a strength parameter comprising matrix tensile strength +.>Compression strength of matrix->Shear Strength of matrix->；
The plastic yielding behavior of the matrix is passed throughYield model calculation:
（5）
in the formula (5), the amino acid sequence of the compound,is hydrostatic pressure, +>Is a linear yielding surface>Friction angle on stress plane +.>For cohesive strength, < >>As the third invariant of the bias stress +.>Is->Equivalent stress (S)>For indirectly representing the flow stress ratio of the Lodel angle, < >>Is the ratio of the triaxial tensile yield stress to the triaxial compressive yield stress.
Preferably, in step S4, the periodic boundary conditions are as follows:
（6）
in the method, in the process of the invention,for displacement in three directions->For RVE geometric length in three directions, +.>Is the relative displacement of the corresponding node.
Therefore, the invention adopts the reverse multi-scale method for representing the composite material fiber-matrix interface damage, and has the following technical effects: when the macroscopic structure of the composite material is not failed, the microscopic structure of the composite material is damaged by the fiber-matrix interface, a macroscopic-microscopic multi-scale damage characterization method is developed for the field of multi-scale computational mechanics of the composite material, and the method has important significance for predicting the sealing failure of the pressure vessel of the composite material based on microscopic scale.
The technical scheme of the invention is further described in detail through the drawings and the embodiments.
Drawings
FIG. 1 is a schematic diagram of the present invention;
FIG. 2 is a grid partition of a composite laminate;
FIG. 3 is a ply sequence diagram of a composite laminate;
figure 4 is a fiber random distribution RVE;
FIG. 5 is a graph of stress concentration areas of a composite laminate;
FIG. 6 is a hole edge area failure condition;
figure 7 is a layer 1 shear failure RVE damage result; wherein a is the damage morphology; b is a shear stress-shear strain graph;
FIG. 8 is a graph of the results of layer 4 tensile failure RNE damage, where a is the failure morphology; b is a tensile stress-tensile strain plot.
Detailed Description
The technical scheme of the invention is further described below through the attached drawings and the embodiments.
Unless defined otherwise, technical or scientific terms used herein should be given the ordinary meaning as understood by one of ordinary skill in the art to which this invention belongs.
Example 1
As shown in fig. 1, a reverse multi-scale method of characterizing composite fiber-matrix interfacial failure, comprising the steps of:
s1, selecting a macroscopic structure of a composite material, and determining the volume fraction of fibersThe engineering elastic constant and the strength of each direction of the material;
s2, applying load to the composite material macrostructure in the step S1, determining a weak area, judging the failure condition of the weak area, and extracting the strain component of the weak area of the composite material macrostructure by checking the strain component of the integral point of the failure unit;
s3, generating fiber volume fraction according to a fiber random distribution RVE generation algorithm on a mesoscopic structureThe random distribution RVE of the fibers, and determining the fiber structure and material parameters, the matrix structure and material parameters;
s4, applying periodic boundary conditions to the random distribution RVE of the fibers to ensure the continuity of the stress and displacement of the microstructure;
s5, applying the strain component of the macrostructure weak area of the composite material extracted in the step S2 to the random fiber distribution RVE of the periodic boundary condition applied in the step S4, and calculating and representing the damage condition of the RVE fiber-matrix interface of the composite material.
In the step S1, the engineering elastic constant of the material comprises an elastic modulus, a shear modulus and a Poisson ratio; the elastic modulus includes 1-direction elastic modulusModulus of elasticity in 2 direction>3 modulus of elasticity>The method comprises the steps of carrying out a first treatment on the surface of the The shear modulus comprises 1-2-direction shear modulus>1-3 shear modulus +.>2-3 shear modulus +.>The method comprises the steps of carrying out a first treatment on the surface of the Poisson's ratio includes 1-2 direction Poisson's ratio->Poisson's ratio in 1-3 direction>Poisson's ratio in 2-3 direction->；
The hoop strength includes tensile strength, compressive strength, and shear strength; tensile strength includes 1-direction tensile strength2-direction tensile Strength->The method comprises the steps of carrying out a first treatment on the surface of the The compressive strength includes 1-direction compressive strength->2-way compression Strength->The method comprises the steps of carrying out a first treatment on the surface of the The shear strength includes 1-2 directional shear strength +.>1-3 shear Strength->And 2-3 direction shear Strength +.>。
In step S2, the failure condition of the weak area is determined according to the maximum stress criterion, the Tsai-Hill criterion, and the Tsai-Wu criterion, which specifically includes the following steps:
（1）
in the formula (1), the components are as follows,is the tensile/compressive strength of the unidirectional sheet 1 in the direction, wherein the tensile strength is +.>Compression is +.>；/>For the unidirectional sheet 2 direction stretching/compression strength, stretching is +.>Compression is +.>；/>Stress in 1 direction>Stress in 2 directions>Stress in the direction of 1-2; />As a failure factor, ++>I.e., composite failure;
the Tsai-Hill criterion is calculated as follows:
（2）
the Tsai-Wu criterion calculation formula is as follows:
（3）
in the formula (3), the coefficients are defined as follows:
（4）。
preferably, in step S3, the fiber is basically a transverse isotropic material, and the material parameter is engineering elastic constant 、/> 、/> 、/> 、/>And->；
The matrix is basically made of isotropic elastoplastic material, and the material parameters comprise engineering elastic constants 、/> 、/>And a strength parameter comprising matrix tensile strength +.>Compression strength of matrix->Shear Strength of matrix->；
The plastic yielding behavior of the matrix is passed throughYield model calculation:
（5）
in the formula (5), the amino acid sequence of the compound,is hydrostatic pressure, +>Is a linear yielding surface>Friction angle on stress plane +.>For cohesive strength, < >>As the third invariant of the bias stress +.>Is->Equivalent stress (S)>For indirectly representing the flow stress ratio of the Lodel angle, < >>Is three in threeRatio of the axial tensile yield stress to the triaxial compressive yield stress.
In step S4, the periodic boundary conditions are as follows:
（6）
in the method, in the process of the invention,for displacement in three directions->For RVE geometric length in three directions, +.>Is the relative displacement of the corresponding node.
The method according to the invention is described below by way of a specific example.
On a macroscopic structure, a geometric model of the composite laminated plate is established according to the open pore stretching standard of the composite laminated plate specified in GB/T30968.3-2014 and HB 6750-1993, the mesh division is shown in figure 2, the material size is 250mm multiplied by 36mm multiplied by 2mm, the hole diameter is 6mm, the global mesh size is 2mm, and the hole edge area is thinned to 1.5mm. The ply sequence of the composite material laminated plate is shown in figure 3, and the ply sequence is set as a symmetrical and balanced ply sequence：
On the mesostructure, a random distribution RVE of fibers with a geometry of 31um x 1um is generated according to a random distribution RVE generation algorithm of fibers, as shown in fig. 4. Fiber diameter 5um, fiber number 29, fiber volume fractionIs consistent with the macrostructure. Furthermore, to ensure stress and displacement continuity of the RVE, periodic boundary conditions are imposed on it.
Macroscopic parameters of carbon fiber composite
Single layer representation of carbon fiber laminateFor transverse isotropy, the material is chosen as，/>59%. The material parameters are shown in table 1.
TABLE 1 carbon fiber laminateParameters (parameters)
。
Microscopic parameters of carbon fiber composite
The mesoscopic parameters are mainly fibers and matrix, as shown in tables 2 and 3.
TABLE 2 carbon fiber IM7 parameters
；
Table 3 matrix 8552 epoxy parameters
。
Calculation result of reverse multi-scale method
First, a displacement load of 1.5mm was applied to the composite laminate in the longitudinal direction. Then, adopting the maximum stress criterion,Criterion and->The guidelines calculate the macroscopic composite laminate strength. After loading, the hole edge is found to be a weak area (namely a stress concentration area), and the stress concentration condition is shown in fig. 5.
The failure condition of the stress concentration area at the hole edge is checked according to different failure criteria, and the result is shown in fig. 6. As can be seen from the results of figure 6,for 8 different layers, the maximum stress criterion,Criterion and->The guidelines showed that both 45 ° ply and-45 ° ply failed, but neither 0 ° ply nor 90 ° ply failed.
Macroscopic failure criteria can characterize the overall failure of the structure, but evenCriteria can characterize the destruction of the fiber and matrix, and also the destruction of the fiber-matrix interface on a microscopic scale. For this purpose, the macroscopic structure pore edge stress concentration region can be strain loaded into the microscopic RVE structure by a reverse multi-scale method, so as to characterize the fiber-matrix interface damage. According to the stress concentration area at the hole edge, according to the layering sequence of 1-8 layers>Extracting stress concentration region unit integration point strain +.>，/>，/>As shown in table 4.
TABLE 4 stress concentration area strain at hole edges
；
As is clear from Table 4, the strain was uniformly and symmetrically distributed, and therefore, layers 1 to 4 were examined. Of these, only layers 1 and 3 failed. Because the strain components of the 1 st layer and the 3 rd layer are consistent in size, the 1 st layer is only required to be loaded to RVE, the 1 st layer failure can be found to be shear failure, the failure morphology is shown in figure 7, the fiber-matrix interface is basically completely destroyed in a stress concentration area, RVE fracture occurs, and macroscopic failure is caused.
Layer 4 is not failed, but is composed ofCriterion and->The failure factors calculated by the criteria all exceeded 0.9. Thus, three strains of layer 4 were applied to RVE, and it was found that layer 4 did not fail, consistent with the results of fig. 6, but with an interface failure condition, the interface failure morphology is shown in fig. 8. It was thus shown that the RVE microstructure had undergone fiber-matrix interface damage, but the tensile strength was not achieved overall, nor was the stress-strain curve drop during structural failure observed.
Therefore, the reverse multi-scale method for representing the composite material fiber-matrix interface damage is adopted, when the composite material macrostructure does not fail, the fiber-matrix interface damage exists on the microstructure, a macroscopic-microscopic multi-scale damage representing method is developed for the field of composite material multi-scale computational mechanics, and the method has important significance for predicting the sealing failure of the composite material pressure vessel based on microscopic scale.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present invention and not for limiting it, and although the present invention has been described in detail with reference to the preferred embodiments, it will be understood by those skilled in the art that: the technical scheme of the invention can be modified or replaced by the same, and the modified technical scheme cannot deviate from the spirit and scope of the technical scheme of the invention.
Claims (5)
1. A reverse multi-scale method of characterizing composite fiber-matrix interfacial failure, comprising the steps of:
s1, selecting a macroscopic structure of a composite material, and determining the volume fraction of fibersThe engineering elastic constant and the strength of each direction of the material;
s2, applying load to the composite material macrostructure in the step S1, determining a weak area, judging the failure condition of the weak area, and extracting the strain component of the weak area of the composite material macrostructure by checking the strain component of the integral point of the failure unit;
s3, generating fiber volume fraction according to a fiber random distribution RVE generation algorithm on a mesoscopic structureThe random distribution RVE of the fibers, and determining the fiber structure and material parameters, the matrix structure and material parameters;
s4, applying periodic boundary conditions to the random distribution RVE of the fibers to ensure the continuity of the stress and displacement of the microstructure;
s5, applying the strain component of the macrostructure weak area of the composite material extracted in the step S2 to the random fiber distribution RVE of the periodic boundary condition applied in the step S4, and calculating and representing the damage condition of the RVE fiber-matrix interface of the composite material.
2. The reverse multiscale method of characterizing fiber-matrix interfacial failure of composite materials of claim 1, wherein in step S1, the engineering elastic constants of the materials include elastic modulus, shear modulus, and poisson' S ratio; the elastic modulus includes 1-direction elastic modulusModulus of elasticity in 2 direction>3 modulus of elasticity>The method comprises the steps of carrying out a first treatment on the surface of the The shear modulus includes 1-2 direction shear modulus +.>1-3 shear modulus +.>2-3 shear modulus +.>The method comprises the steps of carrying out a first treatment on the surface of the Poisson's ratio includes 1-2 direction Poisson's ratio->Poisson's ratio in 1-3 direction>Poisson's ratio in 2-3 direction->；
The hoop strength includes tensile strength, compressive strength, and shear strength; tensile strength includes 1-direction tensile strength2-direction tensile Strength->The method comprises the steps of carrying out a first treatment on the surface of the The compressive strength includes 1-direction compressive strength->2-way compression Strength->The method comprises the steps of carrying out a first treatment on the surface of the The shear strength includes 1-2 directional shear strength +.>1-3 shear Strength->And 2-3 direction shear Strength +.>。
3. The method according to claim 1, wherein in step S2, the failure condition of the weak area is determined by maximum stress criterion, tsai-Hill criterion, tsai-Wu criterion, specifically as follows:
（1）
in the formula (1), the components are as follows,is the tensile/compressive strength of the unidirectional sheet 1 in the direction, wherein the tensile strength is +.>Compression is +.>；/>For the unidirectional sheet 2 direction stretching/compression strength, stretching is +.>Compression is +.>；/>Stress in 1 direction>Is a stress in the direction of 2,stress in the direction of 1-2; />As a failure factor, ++>I.e., composite failure;
the criterion calculation formula is as follows:
（2）
the criterion calculation formula is as follows:
（3）
in the formula (3), the coefficients are defined as follows:
（4）。
4. the method of claim 1, wherein in step S3, the fibers are substantially formed as transverse isotropic materials, and the parameters of the materials are engineering elastic constants 、/> 、 、/> 、/>And->；
The matrix is basically made of isotropic elastoplastic material, and the material parameters comprise engineering elastic constants 、/> 、/>And a strength parameter comprising matrix tensile strength +.>Compression strength of matrix->Shear Strength of matrix->；
The plastic yielding behavior of the matrix is passed throughYield model calculation:
（5）
in the formula (5), the amino acid sequence of the compound,is hydrostatic pressureForce (I) of>Is a linear yielding surface>Friction angle on stress plane +.>For cohesive strength, < >>As the third invariant of the bias stress +.>For Mises equivalent stress, +.>For indirectly representing the flow stress ratio of the Lodel angle, < >>Is the ratio of the triaxial tensile yield stress to the triaxial compressive yield stress.
5. A reverse multiscale method of characterizing fiber-matrix interfacial failure in composite material according to claim 1, wherein in step S4, the periodic boundary conditions are as follows:
（6）
in the method, in the process of the invention,for displacement in three directions->For the geometric length of the RVE in three directions,is the relative displacement of the corresponding node.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311078382.5A CN116796577A (en) | 2023-08-25 | 2023-08-25 | Reverse multi-scale method for representing composite material fiber-matrix interface damage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311078382.5A CN116796577A (en) | 2023-08-25 | 2023-08-25 | Reverse multi-scale method for representing composite material fiber-matrix interface damage |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116796577A true CN116796577A (en) | 2023-09-22 |
Family
ID=88044208
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311078382.5A Pending CN116796577A (en) | 2023-08-25 | 2023-08-25 | Reverse multi-scale method for representing composite material fiber-matrix interface damage |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116796577A (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107356478A (en) * | 2017-07-07 | 2017-11-17 | 吉林大学 | Long fiber reinforced thermoplastic composites Multiscale Simulation Method |
| CN110175419A (en) * | 2019-05-30 | 2019-08-27 | 新疆大学 | Fan blade composite material mesomechanics damage development analysis method |
| CN112528415A (en) * | 2020-12-18 | 2021-03-19 | 沈阳航空航天大学 | Macro-meso failure mode analysis method for composite material shaft structure |
| CN112632819A (en) * | 2020-12-18 | 2021-04-09 | 沈阳航空航天大学 | Method for predicting basic mechanical property parameters of continuous fiber reinforced composite material |
| CN113420376A (en) * | 2021-06-17 | 2021-09-21 | 吉林大学 | Multi-scale-based impact-resistant mechanical property simulation method for carbon fiber composite material |
| CN114861398A (en) * | 2022-04-01 | 2022-08-05 | 中国人民解放军火箭军工程大学 | Method for predicting macroscopic mechanical property of fiber reinforced composite material |
| CN116386776A (en) * | 2023-02-23 | 2023-07-04 | 河南农业大学 | Flax fiber composite material high-low temperature mechanical property prediction method |
-
2023
- 2023-08-25 CN CN202311078382.5A patent/CN116796577A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107356478A (en) * | 2017-07-07 | 2017-11-17 | 吉林大学 | Long fiber reinforced thermoplastic composites Multiscale Simulation Method |
| CN110175419A (en) * | 2019-05-30 | 2019-08-27 | 新疆大学 | Fan blade composite material mesomechanics damage development analysis method |
| CN112528415A (en) * | 2020-12-18 | 2021-03-19 | 沈阳航空航天大学 | Macro-meso failure mode analysis method for composite material shaft structure |
| CN112632819A (en) * | 2020-12-18 | 2021-04-09 | 沈阳航空航天大学 | Method for predicting basic mechanical property parameters of continuous fiber reinforced composite material |
| CN113420376A (en) * | 2021-06-17 | 2021-09-21 | 吉林大学 | Multi-scale-based impact-resistant mechanical property simulation method for carbon fiber composite material |
| CN114861398A (en) * | 2022-04-01 | 2022-08-05 | 中国人民解放军火箭军工程大学 | Method for predicting macroscopic mechanical property of fiber reinforced composite material |
| CN116386776A (en) * | 2023-02-23 | 2023-07-04 | 河南农业大学 | Flax fiber composite material high-low temperature mechanical property prediction method |
Non-Patent Citations (4)
| Title |
|---|
| 左卫刚: "基于Python语言的复合材料结构建模程序建构及其数值模拟", 《新型工业化》, vol. 9, no. 5 * |
| 张笑闻 等: "考虑界面相的低温复合材料结构多尺度分析", 《机械强度》, vol. 43, no. 6, pages 85 - 86 * |
| 沙云东 等: "含界面SiC/TC4复合材料拉伸强度预测及试验验证", 《设计与研究》, no. 7 * |
| 骆丽 等: "纤维增强涡轮轴结构失效模式分析方法及试验验证", 《航空动力学报》 * |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Du et al. | Open-hole tensile progressive damage and failure prediction of carbon fiber-reinforced PEEK–titanium laminates | |
| Shi et al. | Damage characteristics analysis of GFRP-Balsa sandwich beams under Four-point fatigue bending | |
| Zhang et al. | High strain rate compressive behaviors and adiabatic shear band localization of 3-D carbon/epoxy angle-interlock woven composites at different loading directions | |
| İçten et al. | Failure analysis of woven kevlar fiber reinforced epoxy composites pinned joints | |
| Zhang et al. | Research in failure behaviors of hybrid single lap aluminum-CFRP (plain woven) joints | |
| Liu et al. | Mechanical response of a novel composite Y-frame core sandwich panel under shear loading | |
| CN111062117A (en) | Composite laminated plate mixed type interlayer crack propagation analysis method | |
| Deniz et al. | Determination of fatigue life of the unidirectional GFRP/Al hybrid composite laminates | |
| Zhang et al. | Characterizing the off-axis dependence of failure mechanism in notched fiber metal laminates | |
| Liu et al. | Compression property of a novel lattice sandwich structure | |
| Taniguchi et al. | Dynamic tensile properties of carbon fiber composite based on thermoplastic epoxy resin loaded in matrix-dominant directions | |
| Cinar et al. | Effect of residual stress on the bending response of L-shaped composite laminates | |
| Liu et al. | An enhanced elastoplastic damage coupled model for compression characteristics analysis of continuous fiber-reinforced thermoplastic composite stiffened panel | |
| Yang et al. | Compressive behaviour of wood-filled GFRP square columns with lattice-web reinforcements | |
| Zheng et al. | Experimental and numerical studies on the tensile behaviors of thin-ply and thick-ply open-hole laminates | |
| CN111310364B (en) | Laminated plate damage tolerance characterization method with delamination area as evaluation index | |
| CN116796577A (en) | Reverse multi-scale method for representing composite material fiber-matrix interface damage | |
| Bordreuil et al. | Finite element computation of woven ply laminated composite structures up to rupture | |
| Chamis et al. | Defect/damage tolerance of pressurized fiber composite shells | |
| Zhang et al. | Investigation of mechanical performances of composite bolted joints with local reinforcements | |
| Zhang et al. | Buckling and post-buckling characteristics of axially loaded channel-section CFRP/aluminum laminate profiles under the influence of impact damage | |
| Cai et al. | A new interfacial model for transverse mechanical properties of unidirectional fiber reinforced composites | |
| Bougherara et al. | Investigation and modeling of the fatigue damage in natural fiber composites | |
| Amaya | Progressive damage and failure model for composite laminates under multiaxial loading conditions | |
| Vallons et al. | Fibre orientation effects on the tensile properties of biaxial carbon/epoxy NCF composites |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |