Peridynamic Open-Hole Tensile Strength Prediction of Fiber-Reinforced Composite Laminate Using Energy-Based Failure Criteria

In the present study, peridynamic (PD) open-hole tensile (OHT) strength prediction of fiber-reinforced composite laminate using energy-based failure criteria is conducted. Spherical-horizon peridynamic laminate theory (PDLT) model is used. Energy-based failure criteria are introduced into the model. Delamination fracture modes can be distinguished in the present energy-based failure criteria. .ree OHT testing results of fiber-reinforced composite laminate are chosen from literatures and used as benchmarks to validate the present PD composite model with energy-based failure criteria. It is shown that the PD predicted OHTstrength 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 energy-based failure criteria.


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][3][4].It is a nonlocal extension of classical continuum mechanics using spatial integral equations instead of spatial differential equations.e 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 fiber-reinforced 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 low-velocity impact.Kilic et al. [8] predicted the damage in center-cracked 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 homogenization-based 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 fiber-reinforced composite materials subjected to mechanical and thermal loading conditions.Damage growth patterns of preexisting crack in fiber-reinforced 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.e 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 bond-based 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 rate-dependent constitutive equation and a new interlayer bond describing interlayer interactions of fiber-reinforced 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 fiber-reinforced composites under cyclic loading.Jiang and Wang [21] extended the peridynamic laminate theory (PDLT) model by using a spherical horizon instead of adjacent-layer horizon and studied the open-hole 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 low-velocity impact damage on composite laminates with z-pins.Zhou and Liu [24] studied the application of PD in analyzing the impact-induced delamination in laminated composite materials.
Open-hole tensile strength (OHT) of fiber-reinforced 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 fiber-reinforced 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][28][29].On the other hand, standard OHT test results also provide good benchmarks for validating PD composite models.
e 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 adjacent-layer horizon and illustrated that transverse Poisson's effect can be taken into account.In the present study, energy-based failure criteria are introduced into the previous PD composite model.e energy-based failure criteria are derived following the approach proposed by Silling and Lehoucq [4].Delamination fracture modes are distinguished in the present energy-based failure criteria.ree fiber-reinforced composite OHT testing results from published literatures are modeled by using the present PD composite model with energy-based failure criteria.e PD OHTpredicted results are compared with testing results, and the PD OHT displacement field and damage modes are illustrated.
e numerical analysis in the present study is carried out via GPU-parallel computing using PGI CUDA FORTRAN compiler.

Governing Equation.
A three-dimensional 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 v 13 and v 23 can be considered in this PD composite model.e governing equation of this PD composite model is expressed as where , and n denotes the layer number of laminates, as shown in Figure 1.b (n)  (k) is the external load density.t (k)(j) and t (j)(k) are PD force density between x (n)  (k) and x (j) , here x (j) includes both in-plane material points and out-of-plane material points.e PD force density can be expressed as with where denotes the inplane fiber direction or in-plane transverse direction bond stretch, and δ is the radius of the horizon zone.e direction cosines of the relative position vectors between the material 2 Advances in Materials Science and Engineering points x (n) (k) and x (j) in the undeformed and deformed states are defined as e three-dimensional PD dilatation θ (k) can be expressed as ( e 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, in-plane fiber direction, and in-plane transverse direction, respectively.ese parameters are related to material properties of composite laminates, horizon radius, and ply direction.e derivation procedures to get these PD material parameters can be found in [21].
where C 11 , C 22 , C 33 , and C 55 are coefficients of composite material stiffness matrix C, and are defined as 2.2.Energy-Based 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], energy-based failure criteria for delamination damage of fiber-reinforced composites are proposed.is 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 mode-I delamination).Suppose a plane A separates two halves of a threedimensional body B into B + and B − .e delamination front area a is on the plane.Consider a mode-I delamination motion with velocity field on Figure 2. e total energy E absorbed by P in this motion is Advances in Materials Science and Engineering e assumed critical bond breakage work w IC in this motion is erefore, When the critical energy release rate is reached, Similarly, we can get the critical bond breakage work for mode-II and mode-III delamination as From the above derivation, energy-based failure criteria for delamination damage are proposed,  Advances in Materials Science and Engineering for mode-III delamination.
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.
e critical stretches for the fiber bonds and matrix bonds can be calculated by where X T , X C , Y T , and Y C 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.e local damage at a point can be quantified as [3,19] e status variable, μ, 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.
164. 3 [26,34].φ fiber breakage � 1 − where J is the number of fiber material points inside the horizon, N (n) (k) is the number of matrix material points inside the horizon, N 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.

Numerical Implementation
Although the peridynamic governing equation is in dynamic form, it can still be used to solve quasi-static or static problems by using the adaptive dynamic relaxation (ADR) method [32].
According to the ADR method, equation (1) at the nth iteration can be rewritten: where D is the fictitious diagonal density matrix and c is the damping coefficient which can be expressed by in which 1 K n is the diagonal "local" stiffness matrix, which is given as where F n i is the value of force vector F n at material point x, which includes both the peridynamic force state vector and external forces, and λ ii is the diagonal elements of D which should be large enough to avoid numerical divergence.Advances in Materials Science and Engineering By utilizing central-difference explicit integration, displacements, and velocities for the next time step can be obtained: To start the iteration process, we assume that U 0 ≠ 0 and _ U 0 � 0, so the integration can be started by the following equation: Due to the large computational amount of PD model, GPU-parallel computing is introduced.
e PGI CUDA FORTRAN compiler, PGI/17.10Community Edition, is used for compiling.e GPU node at Cranfield University Delta HPC Cluster is applied for running the GPU-parallel program.e GPU block threads are fixed to 256, and the number of blocks is depending on the total number of parallel processes [33].

Summary of the Testing Specimens.
e schematic of open-hole tensile test specimen is shown in Figure 3. ree OHT testing specimens are chosen from the published literatures and renumbered as OHT1, OHT2, and OHT3 as shown in Table 1.
e material system, dimensions, and layup of these specimens are also listed in Table 1.e intralayer and interlayer material properties of each material system are shown in Tables 2-5.

OHT1
[90/45/0/-45] S .Due to the large computational cost of PD, the quarter (1/4) model is used for modeling.e 1/ 4 model mesh size for OHT1 is 254 × 64 × 8. e PD predicted load-displacement for the test is shown in Figure 4. e 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%.
e PD predicted displacement field is shown in Figure 5. e fracture surface is very clearly detected from displacement field U1, which is relatively hard to see in FEM.ree typical damage patterns: fiber breakage, matrix crack for each layer, and delamination between each layer of Advances in Materials Science and Engineering OHT1, are shown in Figures 6-8.It can be seen that the most obvious fiber breakage is in 0 °plies, and the interaction of the three damage modes leads to the final failure of the specimen.9. e 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%.e fracture surface is along the hole edge in x direction.
ree 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 ply-5# (0 °). e final failure of OHT2 happens mainly due to matrix crack and delamination.e 1/4 model mesh size for OHT3 is 382 × 138 × 24. e PD predicted load-displacement for the test is shown in Figure 14. e 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%.
e PD predicted displacement field is shown in Figure 15.e fracture surface is also very clearly detected from displacement field U1. ree 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 0 °plies as OHT1, and the interaction of the three damage modes leads to the final failure of the specimen.

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 open-hole tensile strength of fiber-reinforced composite laminate.e fracture surface can be clearly detected by displacement field in loading direction.ree typical damage modes of fiberreinforced composite laminate: fiber breakage, matrix crack, and delamination can also be captured.Advances in Materials Science and Engineering

Figure 2 :Figure 3 :
Figure 2: Surface energy by the total work absorbed by P − separated from B + for mode-I delamination [4].

Figure 16 :
Figure 16: Fiber breakage for each layer of OHT3.

Figure 17 :
Figure 17: Matrix crack for each layer of OHT3.
Open-hole 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 energy-based failure criteria.Different fracture modes for delamination damage can be distinguished in these energybased failure criteria.reeOHT testing results of fiberreinforced composite laminate are chosen from the literature and modeled by the present PD composite model with energy-based failure criteria.It is shown that the present PD composite mode with energy-based failure criteria can accurately predict the OHT strength of fiber-reinforced composite laminate.efracture surface can be clearly detected.etypical failure modes of composite, fiber breakage, matrix crack, and delamination, are also illustrated in detail for the three testing specimens.enumerical results in the present study validate the accuracy and reliability of the current PD composite model with energybased failure criteria.

Table 1 :
Specimen configuration of composite laminates with open-hole.

Table 6 :
Open-hole tensile strength prediction of fiber-reinforced composite laminates.

Table 7 :
Comparison of predicted open-hole tensile strength of OHT2 with other peridynamic models (MPa).