# New Two-Dimensional Polynomial Failure Criteria for Composite Materials

Authors: Shi Yang Zhao; Pu Xue
Journal: Advances in Materials Science and Engineering
 (2014)

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## Abstract

The in-plane damage behavior and material properties of the composite material are very complex. At present, a large number of two-dimensional failure criteria, such as Chang-Chang criteria, have been proposed to predict the damage process of composite structures under loading. However, there is still no good criterion to realize it with both enough accuracy and computational performance. All these criteria cannot be adjusted by experimental data. Therefore, any special properties of composite material cannot be considered by these criteria. Here, in order to solve the problem that the criteria cannot be adjusted by experiment, new two-dimensional polynomial failure criteria with four internal parameters for composite laminates are proposed in the paper, which include four distinct failure modes: fiber tensile failure, fiber compressive failure, matrix tensile failure, and matrix compressive failure. In general, the four internal parameters should be determined by experiments. One example that identifies parameters of the new failure criteria is given. Using the new criteria can reduce the artificialness of choosing the criteria for the damage simulation of the failure modes in composite laminates.


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## Body

## 1. Introduction

Fiber-reinforced polymer (FRP) composites are widely applied in aerospace, marine, and many other industries due to their lightweight, high stiffness, strength, and damping properties [1]. In order to get strong and reliable structures, it is very important to study the mechanical behavior of FRP. In the studies, the finite element method is proved to be effective and successful which can predict the behavior of composite structures under various loading conditions. From the literatures, many researches can be found on the behavior of composites, such as buckling loads, modal characteristics, damage, and failure. Zhang and Yang [2] gave comprehensive reviews and some of the future research on composite laminated plates. Orifici et al. [3] also gave a critical review to assess the state of the art in material constitutive modeling and composite failure theories. They summarized the various theories and approaches within the context of the dissipated energy framework. The dissipated energy function, with units of energy per unit volume, could be determined from experimental testing and was postulated to be a property of the material. Based on the continuum damage mechanics (CDM), Liu and Zheng [4] reviewed the damage constitutive modeling, the failure criteria, and the finite element implementation in the progressive failure analysis which predicted the stiffness degradation and failure strengths of composite laminates. Specially, the methodologies to solve the numerical convergence problems due to the loss of element stiffness in the finite element analysis were discussed.The failure behavior and damage analysis of the composite laminated structures by the finite element method are paid the most attention by researchers. Michopoulos’s work [5] shows that there is a relationship among many criteria. Hinton et al. [6–11] listed 19 theories of failure criteria proposed for composite laminates and gave a comparison of their predictive capabilities. They showed similarities and differences between the predictions of the 19 theories by comparing the initial and final failure envelopes and representative stress-strain curves. They also explained the differences between the predictions. They did not intend to prove which theory is the best but just clarified their differences between their predictions.Despite a large number of published papers on the damage and failure behavior of the composite laminates under various loadings, a very effective criterion to predict the failure behavior of composites has not achieved yet. Several widely used phenomenological failure criteria, such as the maximum stress, Hoffman, Tsai-Wu, and Tsai-Hill failure criteria [8, 11–14], are proposed to describe the whole ply failure of composite material structures. Other popular phenomenological failure criteria, such as Hashin criteria, Hou criteria, Chang-Chang criteria, Linde criteria, LaRC04 criteria, and Maimí criteria [15–21], can describe the damage process of composite structures in detail, such as fiber breakage, fiber buckling, matrix cracking, therefore, matrix compression. All these criteria cannot be adjusted by experiments. Therefore, any special properties of composite material cannot be considered by these criteria. By studying the problems of dynamic bending failure of composite laminated beams, Santiuste et al. [22] suggested that Hashin criteria may be suitable for ductile composite material, and Hou criteria may be suitable for brittle material in unidirectional laminated beams. Therefore, for different material and different structures, just one failure criterion which cannot be adjusted by experiments could not satisfy various requirements.When we use some known criteria in our study directly, it has used a supposition that material properties used in your own engineering are the same as that in the study which proposed the known criteria. In fact, the failure criteria should be decided by experiments. If one criterion is decided by experiments, the criterion can consider special properties of any material used in engineering. And also, you can use the new failure criteria in numerical simulation to get better numerical results. Here we try to propose new two-dimensional polynomial failure criteria, which can be adjusted by experiments.New two-dimensional polynomial failure criteria with four internal parameters for composite laminates are proposed in the paper. Four distinct failure modes including fiber tensile failure, fiber compressive failure, matrix tensile failure, and matrix compressive failure are considered in the extended criteria. Meanwhile, when some special values are given to the four internal parameters, the extended criteria will become some classical failure criteria such as Chang-Chang criteria, Hashin criteria, and Hou criteria in two-dimensional case. Finally, the features of the failure criteria are discussed in detail. And one example that chooses proper values for the parameters in the criteria is given.


## 2. New Two-Dimensional Failure Criteria

The damage of composite laminates under loading includes intraply failure and interply failure [23]. Intraply failure modes are fiber kinking, fiber fracture, matrix cracking, and matrix-fiber debonding. Interply failure modes are interface cracks between plies.New two-dimensional polynomial failure criteria for composite laminates are with four internal parameters. And each failure mode has a parameter. Therefore, four failure modes all can be adjusted by experiments. And almost special properties of each failure mode can be considered. New two-dimensional polynomial failure criteria are obtained by comparing common and characteristic parts of the present failure criteria, such as Chang-Chang criteria, Hou Criteria, Hashin criteria, and Linde criteria.


### 2.1. Definition of Variables

The related variables include stress components,σ1,σ2,σ12; the tensile damage variable of fiber, dft; the compressive damage variable of fiber, dfc; the tensile damage variable of matrix, dmt; the compressive damage variable of matrix, dmc; some material properties: longitudinal failure stress strength, XT,XC; transverse failure stress strength, YT,Yc; in-plane shear failure stress strength, S12; the subscripts “T” and “C” refer to tension and compression.


### 2.2. Fiber Tensile Failure

Under tension loading, fiber is the main portion to carry load. In composites with high fiber volume fraction and those whose failure strain of the matrix is higher than that of the reinforcing fiber, such as carbon-epoxy composites, longitudinal failures start by isolated fiber fractures in weak zones [20]. The localized fractures increase the normal and interfacial shear stresses in adjoining fiber, and the local stress concentration promotes matrix cracking and fiber and matrix debonding [24].Fiber failure criteria in tension are the most simple damage form for composite laminates. After the accumulation of fracture energy, individual fiber will fail until that the whole ply failure happens. And the whole laminates will carry any loads. In general, the maximum stress strength or strain strength is used to predict fiber failure.A new fiber failure criterion in tensile is(1)dft=k1*(σ1XT)2+(1-k1)*σ1XT+β1σ122/2G12+3/4ασ124S122/2G12+3/4αS124≥1,σ1≥0,
where k1 is a parameter of the criteria of fiber failure; β1 is used to consider the interaction form involving in-plane shear, which can take two values: 0 or 1; α is a parameter for the shear nonlinear effect, which can take two values: 0 or 1.


### 2.3. Fiber Compressive Failure

Under fiber compression loads, laminate failure modes are complex and depend on the material properties. The modes may be microbucking, kinking, and fiber failure [25, 26]. The structures may be in the state of collapse.The criteria for fiber compressive failure are almost the same as the fiber tensile failure, although the failure phenomenon of fiber compressive failure is more complex than the fiber tensile failure.A new fiber failure criterion in compression is(2)dfc=k2*(σ1Xc)2+γ*(k2-1)*σ1Xc+β2*(σ12S)2≥1,σ1≤0,
where k2 is a parameter; β2 is used to consider the interaction form involving in-plane shear, which can take two values: 0 or 1; γ is a parameter which can take two values: 1 and 0.


### 2.4. Failure Criteria for Matrix

Under transverse loading, the behavior of the material is more complex than the fiber failure. A nonlinear stress-strain response will be observed if the laminate is loaded in the transverse direction or in the shear direction. The famous Chang-Chang failure criteria considered the nonlinear shear effects and introduced a coefficient to characterize the nonlinearity. The nonlinear constitutive relation proposed by Richard and Blacklock [27] introduced an exponential degradation form. In general, the fracture plane is perpendicular to the mid-plane of the ply under transverse tensile load. But the angle of the fracture plane will change if transverse stress increases under the compressive load. Generally, for carbon-epoxy and glass-epoxy composites loaded in pure transverse compression, the fracture plane is at an angle of 53°±3° with respect to the thickness direction [20, 28]. The LaRC04 criteria consider the alterative influence of the angle. However, the computational efficiency decreases if the fracture angle changes frequently, so Maimí et al. assumed that the fracture angle can only take one of the two discrete values: 0° or 53° [20].Here, two-dimensional matrix failure criteria for composite materials are expressed by a quadratic polynomial. They will also not include the variable of the mutative fractural angle.


#### 2.4.1. Matrix Tensile Failure

The criteria for matrix tensile failure involve an interaction between the tensile normal and in-plane shear stresses.A new matrix failure criterion in tension is(3)dmt=k3(σ2YT)2+(1-k3)σ2YT+σ122/2G12+3/4ασ124S122/2G12+3/4αS124,xxxxxxxxxxxxxxxxxxxxxxxxxxxxxxxxxσ2≥0,
where k3 is a parameter; α is used to consider the nonlinear interaction form involving in-plane shear.


#### 2.4.2. Matrix Compressive Failure

The criteria for matrix tensile failure are complex in Hashin criteria, Hou criteria, and Chang-Chang criteria. The coefficients of quadratic polynomials are different. Therefore, it is advisable to define the matrix failure criterion in compression with parameters. Parameters should be chosen by experiments.A new matrix failure criterion in tension is as follows:(4)dmc=k4(σ2Yc)2+(k4-1)σ2Yc+σ122/2G12+3/4ασ124S122/2G12+3/4αS124,xxxxxxxxxxxxxxxxxxxxxxxxxxxxxxxxxσ2≤0,
where k4 is a parameter; α is used to consider the nonlinear interaction form involving in-plane shear.So far, the two-dimensional failure criteria for composite materials are given.


## 2.1. Definition of Variables

The related variables include stress components,σ1,σ2,σ12; the tensile damage variable of fiber, dft; the compressive damage variable of fiber, dfc; the tensile damage variable of matrix, dmt; the compressive damage variable of matrix, dmc; some material properties: longitudinal failure stress strength, XT,XC; transverse failure stress strength, YT,Yc; in-plane shear failure stress strength, S12; the subscripts “T” and “C” refer to tension and compression.


## 2.2. Fiber Tensile Failure

Under tension loading, fiber is the main portion to carry load. In composites with high fiber volume fraction and those whose failure strain of the matrix is higher than that of the reinforcing fiber, such as carbon-epoxy composites, longitudinal failures start by isolated fiber fractures in weak zones [20]. The localized fractures increase the normal and interfacial shear stresses in adjoining fiber, and the local stress concentration promotes matrix cracking and fiber and matrix debonding [24].Fiber failure criteria in tension are the most simple damage form for composite laminates. After the accumulation of fracture energy, individual fiber will fail until that the whole ply failure happens. And the whole laminates will carry any loads. In general, the maximum stress strength or strain strength is used to predict fiber failure.A new fiber failure criterion in tensile is(1)dft=k1*(σ1XT)2+(1-k1)*σ1XT+β1σ122/2G12+3/4ασ124S122/2G12+3/4αS124≥1,σ1≥0,
where k1 is a parameter of the criteria of fiber failure; β1 is used to consider the interaction form involving in-plane shear, which can take two values: 0 or 1; α is a parameter for the shear nonlinear effect, which can take two values: 0 or 1.


## 2.3. Fiber Compressive Failure

Under fiber compression loads, laminate failure modes are complex and depend on the material properties. The modes may be microbucking, kinking, and fiber failure [25, 26]. The structures may be in the state of collapse.The criteria for fiber compressive failure are almost the same as the fiber tensile failure, although the failure phenomenon of fiber compressive failure is more complex than the fiber tensile failure.A new fiber failure criterion in compression is(2)dfc=k2*(σ1Xc)2+γ*(k2-1)*σ1Xc+β2*(σ12S)2≥1,σ1≤0,
where k2 is a parameter; β2 is used to consider the interaction form involving in-plane shear, which can take two values: 0 or 1; γ is a parameter which can take two values: 1 and 0.


## 2.4. Failure Criteria for Matrix

Under transverse loading, the behavior of the material is more complex than the fiber failure. A nonlinear stress-strain response will be observed if the laminate is loaded in the transverse direction or in the shear direction. The famous Chang-Chang failure criteria considered the nonlinear shear effects and introduced a coefficient to characterize the nonlinearity. The nonlinear constitutive relation proposed by Richard and Blacklock [27] introduced an exponential degradation form. In general, the fracture plane is perpendicular to the mid-plane of the ply under transverse tensile load. But the angle of the fracture plane will change if transverse stress increases under the compressive load. Generally, for carbon-epoxy and glass-epoxy composites loaded in pure transverse compression, the fracture plane is at an angle of 53°±3° with respect to the thickness direction [20, 28]. The LaRC04 criteria consider the alterative influence of the angle. However, the computational efficiency decreases if the fracture angle changes frequently, so Maimí et al. assumed that the fracture angle can only take one of the two discrete values: 0° or 53° [20].Here, two-dimensional matrix failure criteria for composite materials are expressed by a quadratic polynomial. They will also not include the variable of the mutative fractural angle.


### 2.4.1. Matrix Tensile Failure

The criteria for matrix tensile failure involve an interaction between the tensile normal and in-plane shear stresses.A new matrix failure criterion in tension is(3)dmt=k3(σ2YT)2+(1-k3)σ2YT+σ122/2G12+3/4ασ124S122/2G12+3/4αS124,xxxxxxxxxxxxxxxxxxxxxxxxxxxxxxxxxσ2≥0,
where k3 is a parameter; α is used to consider the nonlinear interaction form involving in-plane shear.


### 2.4.2. Matrix Compressive Failure

The criteria for matrix tensile failure are complex in Hashin criteria, Hou criteria, and Chang-Chang criteria. The coefficients of quadratic polynomials are different. Therefore, it is advisable to define the matrix failure criterion in compression with parameters. Parameters should be chosen by experiments.A new matrix failure criterion in tension is as follows:(4)dmc=k4(σ2Yc)2+(k4-1)σ2Yc+σ122/2G12+3/4ασ124S122/2G12+3/4αS124,xxxxxxxxxxxxxxxxxxxxxxxxxxxxxxxxxσ2≤0,
where k4 is a parameter; α is used to consider the nonlinear interaction form involving in-plane shear.So far, the two-dimensional failure criteria for composite materials are given.


## 2.4.1. Matrix Tensile Failure

The criteria for matrix tensile failure involve an interaction between the tensile normal and in-plane shear stresses.A new matrix failure criterion in tension is(3)dmt=k3(σ2YT)2+(1-k3)σ2YT+σ122/2G12+3/4ασ124S122/2G12+3/4αS124,xxxxxxxxxxxxxxxxxxxxxxxxxxxxxxxxxσ2≥0,
where k3 is a parameter; α is used to consider the nonlinear interaction form involving in-plane shear.


## 2.4.2. Matrix Compressive Failure

The criteria for matrix tensile failure are complex in Hashin criteria, Hou criteria, and Chang-Chang criteria. The coefficients of quadratic polynomials are different. Therefore, it is advisable to define the matrix failure criterion in compression with parameters. Parameters should be chosen by experiments.A new matrix failure criterion in tension is as follows:(4)dmc=k4(σ2Yc)2+(k4-1)σ2Yc+σ122/2G12+3/4ασ124S122/2G12+3/4αS124,xxxxxxxxxxxxxxxxxxxxxxxxxxxxxxxxxσ2≤0,
where k4 is a parameter; α is used to consider the nonlinear interaction form involving in-plane shear.So far, the two-dimensional failure criteria for composite materials are given.


## 3. Features of the New Criteria

### 3.1. Unified Expression of Fiber and Matrix Failure Criteria

The new failure criteria for primary damage failure behavior are given above. In fact, the new criteria can be rewritten as a tensor form as follows:(5)dil=ki*(σiXil)2+γi*(1-k)*|σiXil|+βi*(σ122/2G12+3/4αiσ124S122/2G12+3/4αiS124)2≥1,
where ki is a parameter; βi is used to consider the interaction form involving in-plane shear; γi is a parameter which can take two values: 1 and 0; ∥ is the sign of the absolute value; i is used to denote the damage category: fiber or matrix; l is for the stress direction: tensile or compression.


### 3.2. Some Special Forms of the New Criteria

In fact, Chang-Chang criteria, Hou criteria, and so forth are proposed from some special materials, such as carbon/epoxy and graphite epoxy. Therefore, the validity of parameters in these criteria is very limited. All these known criteria are just good at simulating some special material. If more accurate numerical results are needed, the failure criteria of every material should consider their own material properties and be given one set of special values of parameters. And all these parameters are from experiments. When some special values got by experiments are given to four parameters of the new criteria, it will get good numerical results. Meanwhile, when some special values are given to the four internal parameters, the new criteria will become these classical failure criteria such as Chang-Chang criteria, Linde criteria, Hashin criteria, and Hou criteria in two-dimensional case.Whenk1=1, β1=1, α=0; k2=1, β2=0, γ=0; k3=1; k4=(Yc/2/S23)2, the new criteria will become Hashin criteria in two-dimensional case as follows:
(6)dft=(σ1XT)2+(σ12S)2≥1,σ1≥0,dfc=(σ1Xc)2≥1,σ1≤0,dmt=(σ22YT)2+(σ12S12)2,σ22≥0,dmc=(Yc2S23)2(σ22Yc)2+[(Yc2S23)2-1]σ22Yc+(σ12S12)2≥1,σ22<0.Whenk1=1, β1=1, α=0; k2=1, β2=1, γ=0; k3=1; k4=(Yc/2/S12)2, the new criteria will become Hou criteria in two-dimensional case as follows:
(7)dft=1*(σ1XT)2+(1-1)*σ1+(σ12S)2≥1,σ1≥0,dfc=(σ1XT)2+(σ12S)2≥1,σ1≤0,dmt=(σ22YT)2+(σ12S12)2+(σ23S23)2,σ22≥0,dmc=1Yc[(Yc2S12)2-1]σ22+σ2224S122+(σ12S12)2≥1,σ22<0.Whenk1=XT/Xc, β1=0, α=0; k2=Xc/XT, β2=0, γ=1; k3=YT/Yc; k4=Yc/YT, the new criteria will become Linde criteria in two-dimensional case as follows:
(8)df=(1XT-1Xc)σ1+1XTXcσ12,dm=(1YT-1Yc)σ2+1YTYcσ22+(σ12S12)2.Whenk1=1, β1=1, α=1; k2=1, β2=0, γ=0; k3=1; k4=1, the new criteria will become Chang-Chang criteria as follows:
(9)dft=(σ1XT)2+σ122/2G12+3/4ασ124S122/2G12+3/4αS124≥1,σ1≥0,dfc=(σ1Xc)2≥1,σ1≤0,dmt=(σ22YT)2+σ122/2G12+3/4ασ124S122/2G12+3/4αS124,σ22≥0,dmc=(σ22Yc)2+σ122/2G12+3/4ασ124S122/2G12+3/4αS124,σ22≤0.Whenk3=GIc/GIIc, α=0, (3) will be one part of the failure criteria LaR04, shown in (10). GIc,GIIc are the fracture toughness of Mode I and Mode II, respectively,
(10)dmt=GIcGIIc(σ2YT)2+(1-GIcGIIc)σ2Yt+(σ12S12)2,σ2≥0.From (5)–(9), we find that the new criteria with four parameters have enough capability to match the failure criteria which are used widely in the damage analysis of composite materials.The parameters of the new failure criterion can be defined by experimental data to get better numerical results.


## 3.1. Unified Expression of Fiber and Matrix Failure Criteria

The new failure criteria for primary damage failure behavior are given above. In fact, the new criteria can be rewritten as a tensor form as follows:(5)dil=ki*(σiXil)2+γi*(1-k)*|σiXil|+βi*(σ122/2G12+3/4αiσ124S122/2G12+3/4αiS124)2≥1,
where ki is a parameter; βi is used to consider the interaction form involving in-plane shear; γi is a parameter which can take two values: 1 and 0; ∥ is the sign of the absolute value; i is used to denote the damage category: fiber or matrix; l is for the stress direction: tensile or compression.


## 3.2. Some Special Forms of the New Criteria

In fact, Chang-Chang criteria, Hou criteria, and so forth are proposed from some special materials, such as carbon/epoxy and graphite epoxy. Therefore, the validity of parameters in these criteria is very limited. All these known criteria are just good at simulating some special material. If more accurate numerical results are needed, the failure criteria of every material should consider their own material properties and be given one set of special values of parameters. And all these parameters are from experiments. When some special values got by experiments are given to four parameters of the new criteria, it will get good numerical results. Meanwhile, when some special values are given to the four internal parameters, the new criteria will become these classical failure criteria such as Chang-Chang criteria, Linde criteria, Hashin criteria, and Hou criteria in two-dimensional case.Whenk1=1, β1=1, α=0; k2=1, β2=0, γ=0; k3=1; k4=(Yc/2/S23)2, the new criteria will become Hashin criteria in two-dimensional case as follows:
(6)dft=(σ1XT)2+(σ12S)2≥1,σ1≥0,dfc=(σ1Xc)2≥1,σ1≤0,dmt=(σ22YT)2+(σ12S12)2,σ22≥0,dmc=(Yc2S23)2(σ22Yc)2+[(Yc2S23)2-1]σ22Yc+(σ12S12)2≥1,σ22<0.Whenk1=1, β1=1, α=0; k2=1, β2=1, γ=0; k3=1; k4=(Yc/2/S12)2, the new criteria will become Hou criteria in two-dimensional case as follows:
(7)dft=1*(σ1XT)2+(1-1)*σ1+(σ12S)2≥1,σ1≥0,dfc=(σ1XT)2+(σ12S)2≥1,σ1≤0,dmt=(σ22YT)2+(σ12S12)2+(σ23S23)2,σ22≥0,dmc=1Yc[(Yc2S12)2-1]σ22+σ2224S122+(σ12S12)2≥1,σ22<0.Whenk1=XT/Xc, β1=0, α=0; k2=Xc/XT, β2=0, γ=1; k3=YT/Yc; k4=Yc/YT, the new criteria will become Linde criteria in two-dimensional case as follows:
(8)df=(1XT-1Xc)σ1+1XTXcσ12,dm=(1YT-1Yc)σ2+1YTYcσ22+(σ12S12)2.Whenk1=1, β1=1, α=1; k2=1, β2=0, γ=0; k3=1; k4=1, the new criteria will become Chang-Chang criteria as follows:
(9)dft=(σ1XT)2+σ122/2G12+3/4ασ124S122/2G12+3/4αS124≥1,σ1≥0,dfc=(σ1Xc)2≥1,σ1≤0,dmt=(σ22YT)2+σ122/2G12+3/4ασ124S122/2G12+3/4αS124,σ22≥0,dmc=(σ22Yc)2+σ122/2G12+3/4ασ124S122/2G12+3/4αS124,σ22≤0.Whenk3=GIc/GIIc, α=0, (3) will be one part of the failure criteria LaR04, shown in (10). GIc,GIIc are the fracture toughness of Mode I and Mode II, respectively,
(10)dmt=GIcGIIc(σ2YT)2+(1-GIcGIIc)σ2Yt+(σ12S12)2,σ2≥0.From (5)–(9), we find that the new criteria with four parameters have enough capability to match the failure criteria which are used widely in the damage analysis of composite materials.The parameters of the new failure criterion can be defined by experimental data to get better numerical results.


## 4. Identifying Parameters of the New Failure Criteria

The process of identifying parameters of the new failure criteria by experiments is shown here.Biaxial tests of E-glass and carbon fiber reinforced composite laminates were performed by Soden et al. [29]. In biaxial tests, just σ1,σ2, and σ12 can be obtained. Therefore, just parameters k1,k2,k3, and k4 can be identified by experimental data. The other parameters β1,β2,α,γ in the new criteria are not the main items. In fact, γ is used to consider the influence of linear item, σ1, to the fiber tensile damage; β1 is used to consider the influence of shear stress, σ12, to the fiber tensile damage; β2 is used to consider the influence of shear stress, σ12, to the fiber compressive damage; α is used to consider the influence of nonlinear factor of material. The corresponding real values of the parameters of β1,β2,α,γ in Chang-Chang criteria, Linde criteria, Hashin criteria, and Hou criteria in two-dimensional case are almost the same. Therefore, based on the four failure criteria above, the parameters, β1=1, β2=1, α=0, γ=1, are assumed. In order to reduce the complexity of identifying parameters, k1,k2,k3,k4, we just choose the corresponding coefficients of those parameters from Hashin, Hou, Linde, and Chang-Chang criteria, such as k1=1, XT/XC; k2=1, (Xc/XT)2 and Xc/XT; k3=1, YT/Yc and GIc/GIIc; k4=(Yc/2S12)2, 1 or Yc/YT.


### 4.1. Experiments

E-glass and carbon fiber reinforced composite laminates were used in biaxial tests [29]. Their material properties are listed in Tables 1 and 2, respectively.Table 1
Failure strengths of T300/914C.
X
T/Mpa
X
C/Mpa
Y
T/Mpa
Y
C/Mpa
S
12/Mpa
1500
900
27
200
80Table 2
Failure strengths of E-glass/Ly556/HT907/DY063 epoxy.
X
T/Mpa
X
C/Mpa
Y
T/Mpa
Y
C/Mpa
S
12/Mpa
G
I/J/m2
1500
900
27
200
80
165Biaxial failure for unidirectional T300/914C carbon/epoxy lamina is expressed under combined longitudinal and shear loading (σ1 versus σ12). The specimens were in the form of axially wound tubes made from prepreg T300/BSL914C carbon/epoxy. The tubes were tested under combined axial tension or compression and torsion. All the tubes were end reinforced and grips were used to transmit the torque to the tubes [29].Biaxial failure for unidirectional E-glass/Ly556/HT907/DY063 epoxy lamina is expressed under combined transverse and shear loading (σ2 versus σ12). The tubes with filament wound by circumferentially wound were 60 mm in internal diameter and 2 mm in thickness and were constructed from 62% by volume Vetrotes 21*K43 E-glass fiber (Gevetex) rovings and a Ciba-Geigy epoxy resin system Ly556/HT907/DY063 mixed in weight proportions of 100 : 85 : 4. The tubes were cured at 100°C for 2 h and postcurved at 150°C for 2 h [29].


### 4.2. Determination of Parameters

The parameters,β1=1, β2=1, α=0, γ=1, are assumed, which are based on Chang-Chang criteria, Linde criteria, Hashin criteria, and Hou criteria in two-dimensional case. And (1)–(4) of the new criteria should be rewritten as follows.


#### 4.2.1. For Fiber Tensile Failure

Consider(11)dft=k1*(σ1XT)2+(1-k1)*σ1XT+(σ12S12)≥1,σ1≥0,
where k1 is a parameter which can take two values: 1 and XT/XC. The curves of (11) are shown in Figure 1. The curve of k1=1 and the curve of k1=XT/XC are both lying between the experimental data, which are both effective. However, the curve of k1=XT/XC is close to a large number of experimental data above in Figure 1. Therefore, the curve of k1=XT/XC is used for failure analysis of T300/914C carbon/epoxy lamina.Figure 1
Fiber tensile failure envelope.


#### 4.2.2. For Fiber Compressive Failure

Consider(12)dfc=k2*(σ1Xc)2+(k2-1)*σ1Xc+(σ12S12)≥1,σ1≤0,
where k2 is a parameter which can take three values: 1, (Xc/XT)2, and Xc/XT. The curves of (12) are shown in Figure 2. The curve of k2=1 is outmost among all curves in Figure 2, and the experimental data is almost out of the envelope of all curves. The difference of the curve of k2=1 with the data is minimal. Therefore, the value k2=1 should be used for failure analysis of T300/914C carbon/epoxy lamina.Figure 2
Fiber compressive failure envelope.


#### 4.2.3. For Matrix Tensile Failure

Consider(13)dmt=k3*(σ22YT)2+(1-k3)*σ22+(σ12S12)2,σ22≥0,
where k3 is a parameter which can take three values: 1, YT/Yc, and GIc/GIIc. The curves of (13) are shown in Figure 3. The number of the experimental data is just five. The curve of k3=YT/YC is nethermost. Three data are just in the curve of k3=YT/YC, and the difference of the curve k3=YT/YC is minimal. Therefore, the value k3=YT/YC should be used for failure analysis of E-glass/Ly556/HT907/DY063 epoxy lamina.Figure 3
Matrix tensile failure envelope.


#### 4.2.4. For Matrix Compressive Failure

Consider(14)dmc=k4(σ22Yc)2+(k4-1)σ22Yc+(σ12S12)2≥1,σ22<0,
where k4 is a parameter which can take three values: (Yc/2S12)2, 1, or Yc/YT. The curves of (14) are shown in Figure 4. Because of the difference between the strength obtained through experiments and that used in material property, three curves are all not perfect. From Figure 4, the curve of k4=Yc/YT is close to experimental data. Therefore, the value of k4=Yc/YT should be used in failure analysis of E-glass/Ly556/HT907/DY063 epoxy lamina.Figure 4
Matrix compressive failure envelope.From the discussion above, it is found that it is not enough for the damage criterion that has only one set of the parameters. The failure criteria should be adjusted by experimental data for the materials to meet higher accurate requirement.


## 4.1. Experiments

E-glass and carbon fiber reinforced composite laminates were used in biaxial tests [29]. Their material properties are listed in Tables 1 and 2, respectively.Table 1
Failure strengths of T300/914C.
X
T/Mpa
X
C/Mpa
Y
T/Mpa
Y
C/Mpa
S
12/Mpa
1500
900
27
200
80Table 2
Failure strengths of E-glass/Ly556/HT907/DY063 epoxy.
X
T/Mpa
X
C/Mpa
Y
T/Mpa
Y
C/Mpa
S
12/Mpa
G
I/J/m2
1500
900
27
200
80
165Biaxial failure for unidirectional T300/914C carbon/epoxy lamina is expressed under combined longitudinal and shear loading (σ1 versus σ12). The specimens were in the form of axially wound tubes made from prepreg T300/BSL914C carbon/epoxy. The tubes were tested under combined axial tension or compression and torsion. All the tubes were end reinforced and grips were used to transmit the torque to the tubes [29].Biaxial failure for unidirectional E-glass/Ly556/HT907/DY063 epoxy lamina is expressed under combined transverse and shear loading (σ2 versus σ12). The tubes with filament wound by circumferentially wound were 60 mm in internal diameter and 2 mm in thickness and were constructed from 62% by volume Vetrotes 21*K43 E-glass fiber (Gevetex) rovings and a Ciba-Geigy epoxy resin system Ly556/HT907/DY063 mixed in weight proportions of 100 : 85 : 4. The tubes were cured at 100°C for 2 h and postcurved at 150°C for 2 h [29].


## 4.2. Determination of Parameters

The parameters,β1=1, β2=1, α=0, γ=1, are assumed, which are based on Chang-Chang criteria, Linde criteria, Hashin criteria, and Hou criteria in two-dimensional case. And (1)–(4) of the new criteria should be rewritten as follows.


### 4.2.1. For Fiber Tensile Failure

Consider(11)dft=k1*(σ1XT)2+(1-k1)*σ1XT+(σ12S12)≥1,σ1≥0,
where k1 is a parameter which can take two values: 1 and XT/XC. The curves of (11) are shown in Figure 1. The curve of k1=1 and the curve of k1=XT/XC are both lying between the experimental data, which are both effective. However, the curve of k1=XT/XC is close to a large number of experimental data above in Figure 1. Therefore, the curve of k1=XT/XC is used for failure analysis of T300/914C carbon/epoxy lamina.Figure 1
Fiber tensile failure envelope.


### 4.2.2. For Fiber Compressive Failure

Consider(12)dfc=k2*(σ1Xc)2+(k2-1)*σ1Xc+(σ12S12)≥1,σ1≤0,
where k2 is a parameter which can take three values: 1, (Xc/XT)2, and Xc/XT. The curves of (12) are shown in Figure 2. The curve of k2=1 is outmost among all curves in Figure 2, and the experimental data is almost out of the envelope of all curves. The difference of the curve of k2=1 with the data is minimal. Therefore, the value k2=1 should be used for failure analysis of T300/914C carbon/epoxy lamina.Figure 2
Fiber compressive failure envelope.


### 4.2.3. For Matrix Tensile Failure

Consider(13)dmt=k3*(σ22YT)2+(1-k3)*σ22+(σ12S12)2,σ22≥0,
where k3 is a parameter which can take three values: 1, YT/Yc, and GIc/GIIc. The curves of (13) are shown in Figure 3. The number of the experimental data is just five. The curve of k3=YT/YC is nethermost. Three data are just in the curve of k3=YT/YC, and the difference of the curve k3=YT/YC is minimal. Therefore, the value k3=YT/YC should be used for failure analysis of E-glass/Ly556/HT907/DY063 epoxy lamina.Figure 3
Matrix tensile failure envelope.


### 4.2.4. For Matrix Compressive Failure

Consider(14)dmc=k4(σ22Yc)2+(k4-1)σ22Yc+(σ12S12)2≥1,σ22<0,
where k4 is a parameter which can take three values: (Yc/2S12)2, 1, or Yc/YT. The curves of (14) are shown in Figure 4. Because of the difference between the strength obtained through experiments and that used in material property, three curves are all not perfect. From Figure 4, the curve of k4=Yc/YT is close to experimental data. Therefore, the value of k4=Yc/YT should be used in failure analysis of E-glass/Ly556/HT907/DY063 epoxy lamina.Figure 4
Matrix compressive failure envelope.From the discussion above, it is found that it is not enough for the damage criterion that has only one set of the parameters. The failure criteria should be adjusted by experimental data for the materials to meet higher accurate requirement.


## 4.2.1. For Fiber Tensile Failure

Consider(11)dft=k1*(σ1XT)2+(1-k1)*σ1XT+(σ12S12)≥1,σ1≥0,
where k1 is a parameter which can take two values: 1 and XT/XC. The curves of (11) are shown in Figure 1. The curve of k1=1 and the curve of k1=XT/XC are both lying between the experimental data, which are both effective. However, the curve of k1=XT/XC is close to a large number of experimental data above in Figure 1. Therefore, the curve of k1=XT/XC is used for failure analysis of T300/914C carbon/epoxy lamina.Figure 1
Fiber tensile failure envelope.


## 4.2.2. For Fiber Compressive Failure

Consider(12)dfc=k2*(σ1Xc)2+(k2-1)*σ1Xc+(σ12S12)≥1,σ1≤0,
where k2 is a parameter which can take three values: 1, (Xc/XT)2, and Xc/XT. The curves of (12) are shown in Figure 2. The curve of k2=1 is outmost among all curves in Figure 2, and the experimental data is almost out of the envelope of all curves. The difference of the curve of k2=1 with the data is minimal. Therefore, the value k2=1 should be used for failure analysis of T300/914C carbon/epoxy lamina.Figure 2
Fiber compressive failure envelope.


## 4.2.3. For Matrix Tensile Failure

Consider(13)dmt=k3*(σ22YT)2+(1-k3)*σ22+(σ12S12)2,σ22≥0,
where k3 is a parameter which can take three values: 1, YT/Yc, and GIc/GIIc. The curves of (13) are shown in Figure 3. The number of the experimental data is just five. The curve of k3=YT/YC is nethermost. Three data are just in the curve of k3=YT/YC, and the difference of the curve k3=YT/YC is minimal. Therefore, the value k3=YT/YC should be used for failure analysis of E-glass/Ly556/HT907/DY063 epoxy lamina.Figure 3
Matrix tensile failure envelope.


## 4.2.4. For Matrix Compressive Failure

Consider(14)dmc=k4(σ22Yc)2+(k4-1)σ22Yc+(σ12S12)2≥1,σ22<0,
where k4 is a parameter which can take three values: (Yc/2S12)2, 1, or Yc/YT. The curves of (14) are shown in Figure 4. Because of the difference between the strength obtained through experiments and that used in material property, three curves are all not perfect. From Figure 4, the curve of k4=Yc/YT is close to experimental data. Therefore, the value of k4=Yc/YT should be used in failure analysis of E-glass/Ly556/HT907/DY063 epoxy lamina.Figure 4
Matrix compressive failure envelope.From the discussion above, it is found that it is not enough for the damage criterion that has only one set of the parameters. The failure criteria should be adjusted by experimental data for the materials to meet higher accurate requirement.


## 5. Conclusions

In this work, new two-dimensional failure criteria with four parameters for composite materials are given. The new criteria include fiber failure criteria in tension and compression and matrix failure criteria in tension and compression.The new criteria can be adjusted with four parameters to consider different material properties in engineering. In general, when we use some known criteria in our study, it has to assume that our material properties are the same as that in the study which proposed the known criteria. Those problems above can be solved by the new criteria proposed in this paper. Meanwhile, when some special values are given to the four internal parameters, the new criteria have the same expression as some classical failure criteria, such as Chang-Chang criteria, Hashin criteria, Linde criteria, and Hou criteria in two-dimensional case, which are used frequently in the research of damage process for the composite structures.In general, the four internal parameters should be chosen by experiments. One example that chooses proper values for the parameters is given, which also validates that there is no one and only set of value for the parameters in any criterion.



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*Source: 503483-2014-05-28.xml*