Postbuckling response of composite laminated plates with evolving damage

Abstract

In this paper, postbuckling behavior and progressive failure of laminated plates considering geometric nonlinearity and evolving material damage under uniaxial, biaxial compressive and in-plane shear loadings are studied. The damage model is based on a generalized macroscopic continuum theory within the framework of irreversible thermodynamics and enables to predict the progressive damage and failure load. Damage variables are introduced for the phenomenological treatment of degradation of the stiffness properties of laminated plates due to microscopic defects. The analysis is carried out using field-consistent finite element approach based on first-order shear deformation theory. The nonlinear governing equations are solved using the Newton–Raphson iterative technique coupled with the adaptive displacement control method to trace the pre- and postbuckling equilibrium path. The damage evolution equations are solved at every Gauss point using Newton–Raphson iterative technique within each loading/displacement increment iteration. The detailed parametric study is carried out to investigate the influences of evolving damage, span-to-thickness ratio, lamination scheme, boundary conditions and aspect ratio on the postbuckling response and failure load of laminated plates under in-plane loading. The ratio of failure load to buckling load increases with increase in thickness ratio due to the dominating restoring action of in-plane stretching forces in postbuckling region of thin plates whereas the thick plates depict material failure prior to buckling point. Thin plates with SSFF boundary conditions with evolving damage depict softening postbuckling response whereas the plates with other boundary conditions considered depict hardening response.

Review on Local Buckling of Hollow Box FRP Profiles in Civil Structural Applications

“…Reducing the wall slenderness increases the profile stability and buckling capacity exponentially [ 152 , 167 ], and shifts the failure mode from local buckling to material compressive failure due to the increase in the flexural stiffness of the laminated walls [ 170 , 185 ]. The effect of the wall slenderness was studied extensively for laminated plate geometry subjected to uniaxial compressive load [ 133 , 143 , 146 , 152 ] and the effect of the layup properties on the buckling load capacity of slender plates was found to be negligible compared to their dimensions [ 137 , 144 , 153 ]. This finding agrees with the results of parametric studies on open-section PFRP columns [ 67 , 81 , 114 ], shown in Figure 8 .…”

“… The percentage of each research methodology used to study local buckling and its parameters (FEM: finite element method [ 29 , 54 , 55 , 57 , 58 , 66 , 68 , 69 , 71 , 73 , 81 , 88 , 91 , 93 , 94 , 95 , 99 , 106 , 108 , 109 , 110 , 111 , 112 , 113 , 114 , 115 , 131 , 132 , 133 , 134 , 135 , 136 , 137 , 138 , 139 , 140 , 141 , 142 , 143 , 144 , 145 , 146 , 147 , 148 , 149 , 150 , 151 , 152 , 153 , 154 , 155 , 156 , …”

“… The number of publications on the manufacturing design parameters of local buckling for different FRP composite geometries (Wall slenderness: Open-section [ 17 , 66 , 67 , 72 , 75 , 76 , 77 , 81 , 83 , 84 , 87 , 90 , 108 , 109 , 111 ], Plate [ 133 , 137 , 143 , 144 , 145 , 146 , 152 , 153 , 169 ], and Box [ 54 , 76 , 94 ], Cross-sectional aspect ratio: Open-section [ 63 , 64 , 65 , 68 , 69 , 74 , 86 , 111 ] and Box [ 63 , 106 , 108 ], Corner geometry: Open-section [ 61 , 89 ], Fibre angle: Open-section [ 53 , 58 , 74 , 78 , 80 , 87 , 97 , 113 , 114 ], Plate [ 131 , …”

Buckling and postbuckling behaviour of Glare laminates containing splices and doublers. Part 2: Numerical modelling

“…The results indicated that these couplings, especially those relating to stretching and bending behaviour, cause out-of-plane deflections prior to buckling which reduce the buckling load significantly. Further analytical models have been developed [10,11,12,13,14] enabling the prediction of the compression response of laminated composite panels containing single and multiple delaminations. In terms of Fibre Metal Laminates less work has been done.…”