A Progressive Damage Model for Laminated Composites Containing Stress Concentrations

Abstract

A progressive damage model is presented for notched laminated composites subjected to tensile loading. The model is capable of assessing damage in laminates with arbitrary ply-orientations and of predicting the ultimate tensile strength of the notched laminates. The model consists of two parts, namely, the stress analysis and the failure analysis. Stresses and strains in laminates were analyzed on the basis of classical lamination theory with the consideration of material nonlinearity. Damage accumulation in laminates was evaluated by proposed failure criteria combined with a proposed property degradation model. A nonlinear finite element program, based on the model, was developed for lami nates containing a circular hole. Numerical results were compared with the experimental data on laminates containing an open circular hole. An excellent agreement was found be tween the analytical prediction and the experimental data.

Crashworthiness Analysis and Evaluation of Fuselage Section with Sub-floor Composite Sinusoidal Specimens

“…The Chang-Chang failure criterion is used to determine the behavior of MAT54 material (Chang, 1987;Han, 2007;Paolo, 2011;LSTC, 2012), if the material is beyond the elastic region, as follows:…”

Numerical analysis of high velocity impacts on unidirectional laminates

“…The carbon/epoxy unidirectional plies have been modelled using an orthotropic linear elastic behavior until failure, which was modelled using the ChangChang [30] criteria; this model adequately predicts the different damage mechanisms that appear intra-laminar. To model the interaction between the laminas, a cohesive interaction approach has been used to take into account the inter-laminar behaviour.…”

“…Several discrete damage models have been used as failure criteria for layered shell elements representing a laminated composite [27,28]. The most used among these are maximum stress or strain criteria, Hashin [29], Chang-Chang [30] and Hou et al [31], or modifications of those models [12]. Aforementioned models usually involve differentiated damage parameters for one or more of the known failure modes for laminates, such as fiber breaking in tension, fiber buckling in compression, matrix cracking, fiber-matrix debonding or delamination of the composites plies.…”

Simulating Progressive Damage of Notched Composite Laminates with Various Lamination Schemes

“…Chang and Chang [1] was first to propose an FE based progressive damage model to predict tensile strength of laminated composites containing stress concentrations. Progressive damage by partial discount method was introduced by them.…”