Research Article  Open Access
Peridynamic OpenHole Tensile Strength Prediction of FiberReinforced Composite Laminate Using EnergyBased Failure Criteria
Abstract
In the present study, peridynamic (PD) openhole tensile (OHT) strength prediction of fiberreinforced composite laminate using energybased failure criteria is conducted. Sphericalhorizon peridynamic laminate theory (PDLT) model is used. Energybased failure criteria are introduced into the model. Delamination fracture modes can be distinguished in the present energybased failure criteria. Three OHT testing results of fiberreinforced composite laminate are chosen from literatures and used as benchmarks to validate the present PD composite model with energybased failure criteria. It is shown that the PD predicted OHT strength fits the experimental results quite well. From the predicted displacement field, the fracture surface can be clearly detected. Typical damage modes of composite, fiber breakage, matrix crack, and delamination, are also illustrated in detail for each specimen. Numerical results in the present study validate the accuracy and reliability of the present PD composite model with energybased failure criteria.
1. Introduction
Peridynamics (PD) is found to have great advantages in dealing with fracture and damage problems in recent years [1]. Peridynamic theory of solid mechanics is established by Silling et al. [2–4]. It is a nonlocal extension of classical continuum mechanics using spatial integral equations instead of spatial differential equations. The nonlocal and integral features of PD provide a new roadmap for treating discontinuities in fracture and damage problems. Spontaneous crack propagation path can be easily realized in PD without any special treatment of the crack tip [3].
Fracture and damage of fiberreinforced composite (FRC) is a good application area of peridynamics. Fiber breakage, matrix crack, delamination, and the interaction of these damage modes in FRC can cause many discontinuities. Fracture and damage analysis of FRC composite using PD is emerging. Askari et al. [5] analyzed the damage and failure of composite panels under static and dynamics loads. Xu et al. [6, 7] predicted in detail the delamination and matrix damage process in composite laminates under biaxial loads and lowvelocity impact. Kilic et al. [8] predicted the damage in centercracked laminates with different fiber orientations. Oterkus et al. [9] present an approach based on the merger of classical continuum theory and peridynamic theory to predict failure simulations in bolted composite lap joints. Hu et al. [10, 11] proposed a homogenizationbased peridynamic model for simulating fracture and damage in fiberreinforced composites and analyzed the dynamic effects induced by different types of dynamic loading. Oterkus and Madenci [12, 13] present an application of PD theory in the analysis of fiberreinforced composite materials subjected to mechanical and thermal loading conditions. Damage growth patterns of preexisting crack in fiberreinforced composite laminates subjected to tensile loading are computed. Oterkus et al. [14] present an analysis approach based on a merger of the finite element method and the peridynamic theory. The validity of the approach is established through qualitative and quantitative comparisons against the test results for a stiffened composite curved panel with a central slot under combined internal pressure and axial tension. Hu et al. [15] developed a PD composite model that accounts for the variation of bond micromodulus based on the angle between the bond direction and fiber orientation. As an extension of this model, Hu et al. [16] developed an energybased approach to simulate delamination under different fracture mode conditions. Furthermore, Hu and Madenci [17] present a new bondbased peridynamic modeling of composite laminates without any limitation to specific fiber orientation and material properties in order to consider arbitrary laminate layups. Sun and Huang [18] proposed a peridynamic ratedependent constitutive equation and a new interlayer bond describing interlayer interactions of fiberreinforced composite laminate. Diyaroglu et al. [19] demonstrate the applicability of peridynamics to accurately predict nonlinear transient deformation and damage behavior of composites under shock or blast types of loadings due to explosions. Hu and Madenci [20] present an application of peridynamics to predict damage initiation and growth in fiberreinforced composites under cyclic loading. Jiang and Wang [21] extended the peridynamic laminate theory (PDLT) model by using a spherical horizon instead of adjacentlayer horizon and studied the openhole tensile strength of composite laminate. Cuenca and Weckneret al. [22] investigated the application of peridynamics in dynamic fracture simulations for composite structures in high energy dynamic impact (HEDI) events. Baber et al. [23] used PD to model the lowvelocity impact damage on composite laminates with zpins. Zhou and Liu [24] studied the application of PD in analyzing the impactinduced delamination in laminated composite materials.
Openhole tensile strength (OHT) of fiberreinforced composite laminate is an important structural design allowable for composite aircraft. Analysis OHT results are as important as testing results due to overall consideration of cost and reliability for composite structure design. Reliable OHT prediction of fiberreinforced composite laminate is a challenging problem [25, 26]. In the previous studies, PD gives impressive results in OHT prediction of fiberreinforced composite laminates [15, 17, 27–29]. On the other hand, standard OHT test results also provide good benchmarks for validating PD composite models.
The present study is a further investigation of previously proposed PD composite model [21]. In the previous work, we extended the PDLT model [30, 31] by using a spherical horizon instead of adjacentlayer horizon and illustrated that transverse Poisson’s effect can be taken into account. In the present study, energybased failure criteria are introduced into the previous PD composite model. The energybased failure criteria are derived following the approach proposed by Silling and Lehoucq [4]. Delamination fracture modes are distinguished in the present energybased failure criteria. Three fiberreinforced composite OHT testing results from published literatures are modeled by using the present PD composite model with energybased failure criteria. The PD OHT predicted results are compared with testing results, and the PD OHT displacement field and damage modes are illustrated. The numerical analysis in the present study is carried out via GPUparallel computing using PGI CUDA FORTRAN compiler.
2. Ordinary StateBased Peridynamic Model for Composite Laminates
2.1. Governing Equation
A threedimensional PD composite model is proposed by Jiang and Wang [21] in the way of extending the PDLT model [30, 31] to spherical horizon. Transverse Poisson’s ratio and can be considered in this PD composite model. The governing equation of this PD composite model is expressed aswhere is the density of material point , is instantaneous acceleration of , and n denotes the layer number of laminates, as shown in Figure 1. is the external load density. and are PD force density between and , here includes both inplane material points and outofplane material points. The PD force density can be expressed aswithwhere is the stretch of bonds, denotes the inplane fiber direction or inplane transverse direction bond stretch, and is the radius of the horizon zone. The direction cosines of the relative position vectors between the material points and in the undeformed and deformed states are defined as
The threedimensional PD dilatation can be expressed as
The PD material parameters a and d characterize the effect of dilation and b, b_{F}, and b_{T} are associated with deformation of material points in arbitrary directions, inplane fiber direction, and inplane transverse direction, respectively. These parameters are related to material properties of composite laminates, horizon radius, and ply direction. The derivation procedures to get these PD material parameters can be found in [21].where , , , and are coefficients of composite material stiffness matrix , and are defined as
2.2. EnergyBased Failure Criteria
Following the approach for deriving the relationship between the critical bond breakage work and critical energy release rate by Silling and Lehoucq [4], energybased failure criteria for delamination damage of fiberreinforced composites are proposed.
This approach assumes that the energy consumed by a growing delamination front equals the work required, per unit delamination front area, to separate two halves of a body across a plane (Figure 2 for modeI delamination). Suppose a plane separates two halves of a threedimensional body into and . The delamination front area is on the plane. Consider a modeI delamination motion with velocity field on Figure 2. The total energy absorbed by in this motion is
(a)
(b)
The assumed critical bond breakage work in this motion is
Therefore,
When the critical energy release rate is reached,
Similarly, we can get the critical bond breakage work for modeII and modeIII delamination as
From the above derivation, energybased failure criteria for delamination damage are proposed,
Intralayer failure criteria used in the present study is similar to other PD models [15, 17]. When the bond stretch between two material points exceeds a critical value, the interaction between these two material points is irreversibly removed. The critical stretches for the fiber bonds and matrix bonds can be calculated bywhere , , , and are strengths of composite materials.
Local damage at a material point is defined as the weighted ratio of the number of eliminated interactions to the total number of initial interactions of the material point with its family members. The local damage at a point can be quantified as [3, 19]
The status variable, , is defined as
Using the failure criteria presented above, three kinds of typical damage modes of composite laminates can be captured: fiber breakage, matrix cracking, and delamination. These damage modes are indicated bywhere is the number of fiber material points inside the horizon, is the number of matrix material points inside the horizon, is the number of upper side interlayer material points inside the horizon, and is the number of lower side interlayer material points inside the horizon.
3. Numerical Implementation
Although the peridynamic governing equation is in dynamic form, it can still be used to solve quasistatic or static problems by using the adaptive dynamic relaxation (ADR) method [32].
According to the ADR method, equation (1) at the iteration can be rewritten:where is the fictitious diagonal density matrix and is the damping coefficient which can be expressed byin which is the diagonal “local” stiffness matrix, which is given aswhere is the value of force vector at material point , which includes both the peridynamic force state vector and external forces, and is the diagonal elements of which should be large enough to avoid numerical divergence.
By utilizing centraldifference explicit integration, displacements, and velocities for the next time step can be obtained:
To start the iteration process, we assume that and , so the integration can be started by the following equation:
Due to the large computational amount of PD model, GPUparallel computing is introduced. The PGI CUDA FORTRAN compiler, PGI/17.10 Community Edition, is used for compiling. The GPU node at Cranfield University Delta HPC Cluster is applied for running the GPUparallel program. The GPU block threads are fixed to 256, and the number of blocks is depending on the total number of parallel processes [33].
4. Numerical Results
4.1. Summary of the Testing Specimens
The schematic of openhole tensile test specimen is shown in Figure 3. Three OHT testing specimens are chosen from the published literatures and renumbered as OHT1, OHT2, and OHT3 as shown in Table 1. The material system, dimensions, and layup of these specimens are also listed in Table 1. The intralayer and interlayer material properties of each material system are shown in Tables 2–5.




4.2. OHT1 [90/45/0/45]_{S}
Due to the large computational cost of PD, the quarter (1/4) model is used for modeling. The 1/4 model mesh size for OHT1 is . The PD predicted loaddisplacement for the test is shown in Figure 4. The experimental and PD predicted strength is shown in Table 6. As we can see, the relative error of PD predicted strength for OHT1 is −5.19%. The PD predicted displacement field is shown in Figure 5. The fracture surface is very clearly detected from displacement field U1, which is relatively hard to see in FEM. Three typical damage patterns: fiber breakage, matrix crack for each layer, and delamination between each layer of OHT1, are shown in Figures 6–8. It can be seen that the most obvious fiber breakage is in plies, and the interaction of the three damage modes leads to the final failure of the specimen.

(a)
(b)
(c)
4.3. OHT2 [0/45/90/45]_{2S}
The 1/4 model mesh size for OHT2 is . The PD predicted loaddisplacement for the test is shown in Figure 9. The experimental and PD predicted strength is shown in Table 6. As we can see, the relative error of PD predicted strength for OHT2 is 1.82%. Table 7 compares the current model’s result with other Peridynamicbased results. It can be seen that these three peridynamic models all have good accuracy in predicting openhole tensile strength of OHT2, and the model proposed in the present study gives better result than previous models.
The PD predicted displacement field is shown in Figure 10. The fracture surface is along the hole edge in x direction. Three typical damage patterns, fiber breakage, matrix crack for each layer, and delamination between each layer of OHT2 are shown in Figures 11–13. It can be seen that fiber breakage is very few for OHT2, only happens around the hole edge of ply5# (). The final failure of OHT2 happens mainly due to matrix crack and delamination.
(a)
(b)
(c)
4.4. OHT3 [90/0/45/45]_{3S}
The 1/4 model mesh size for OHT3 is . The PD predicted loaddisplacement for the test is shown in Figure 14. The experimental and PD predicted strength is shown in Table 6. As we can see, the relative error of PD predicted strength for OHT3 is 3.92%. The PD predicted displacement field is shown in Figure 15. The fracture surface is also very clearly detected from displacement field U1. Three typical damage patterns, fiber breakage, matrix crack for each layer, and delamination between each layer of OHT3, are shown in Figures 16–18. It can be seen that fiber breakage also happens mainly in plies as OHT1, and the interaction of the three damage modes leads to the final failure of the specimen.
(a)
(b)
(c)
5. Discussion
It can conclude from the numerical results in Sections 4.2–4.4 that the current PD composite model with energybased failure criteria can accurately predict the openhole tensile strength of fiberreinforced composite laminate. The fracture surface can be clearly detected by displacement field in loading direction. Three typical damage modes of fiberreinforced composite laminate: fiber breakage, matrix crack, and delamination can also be captured.
6. Conclusion
Openhole tensile (OHT) strength prediction of fiberreinforced composite laminate is an important and challenging problem. Peridynamics (PD) is proved to have advantages in dealing with fracture and damage of composite. In the present study, we further investigated the previously proposed PD composite model by introducing energybased failure criteria. Different fracture modes for delamination damage can be distinguished in these energybased failure criteria. Three OHT testing results of fiberreinforced composite laminate are chosen from the literature and modeled by the present PD composite model with energybased failure criteria. It is shown that the present PD composite mode with energybased failure criteria can accurately predict the OHT strength of fiberreinforced composite laminate. The fracture surface can be clearly detected. The typical failure modes of composite, fiber breakage, matrix crack, and delamination, are also illustrated in detail for the three testing specimens. The numerical results in the present study validate the accuracy and reliability of the current PD composite model with energybased failure criteria.
Data Availability
Previously reported (experimental) data were used to support this study and are available at http://10.1016/j.compstruct.2016.05.063; http://10.1007/s1070400993338; and http://10.1016/j.compscitech.2007.02.005. These prior studies (and datasets) are cited at relevant places within the text as references [17, 25, 34].
Conflicts of Interest
The authors declare that they have no conflicts of interest.
Acknowledgments
The authors acknowledge the financial support from the China Scholarship Council (CSC No. 201706230169).
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Copyright © 2019 XiaoWei Jiang et al. This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.