Damage Tolerance of Laminated Composites Containing an Open Hole and Subjected to Compressive Loadings: Part I—Analysis

Abstract

An analytical investigation was performed to study the damage in laminated composites containing an open hole and subjccted to compressive loading. A progressive damage model was developed during the inxstigation to predict the extent and the failure modes of the internal damage in the laminates as a function of the applied load and to simulate the in-plane response of the laminates from initial loading to final collapse. The model consists of a stress analysis and a failure analysis. Stresses and strains inside the laminates were calculated by a nonlinear finite element analysis which is based on finite deformation theory with consideration of material and geometric nonlinearities. The types and extent of damage in the material were predicted by a failure analysis which includes a set of proposed failure criteria and material degradation models.Numerical results from the model were compared with the data which were obtained during the investigation and are presented in a companion paper [l]. Good agreements were found between the predictions and the test results. A computer code was developed based on the model which can be used as a tool for sizing and designing composite plates containing holes and subjected to compression. Downloaded from 2. The in-plane response of the plate 3. The compressive strength of the plate 4. The residual stiffness and residual strength of the plates after a prescribed load ANALYTICAL AIODELSince the major interest of this research is in-plane compression failure in laminated composites due to material damage, rather than geometrically related

Analysis of impact response and damage in laminated composite shell involving large deformation and material degradation

“…This difference is generally attributed to the thickness effect of the laminate, adjacent ply constraints and thermal residual stresses [Flaggs and Kural 1982;Peters 1984;Chang and Lessard 1991]. Here empirical relations proposed by [Chang and Lessard 1991] are adopted for calculating in situ ply strengths as a function of the laminate thickness and stacking sequence. These relations are given as…”

On the prediction of bolted single-lap composite joints

“…The most commonly used failure criteria to predict pin joints failure are those based on Chang Chang [21] and Chang Lessard [22] formulations that consider only in plane stresses. Several studies has demonstrated that non linear shear stress strain relationship must be considered to predict pin joints bearing strength [23 26].…”

“…The main goal of this work is the implementation of a new set of failure cri teria to predict bearing strength of bolted single lap composite joints. The proposed set of failure criteria is an extension of Chang Chang [21] and Chang Lessard [22] criteria including the effect of out of plane stresses.…”

Simulating Progressive Damage of Notched Composite Laminates with Various Lamination Schemes

“…However, their model results in underestimation of failure strength in some cases as pointed out by Icten and Karakuzu [2]. Chang and Lessard [3] extended the previous progressive damage model for investigating the compressive failure strength of laminated composites. Researchers like: Lessard and Shokrieh [4], Shahid and Chang [5], Su et al [6], Icten and Karakuzu [2] also studied damage accumulation in composite laminates.…”