Composite shells and panels are widely used in aerospace structures. These are often subjected to defects and damage from both in-service and manufacturing events. Delamination is the most important of these defects. This paper deals with the computational modelling of delamination in a laminated composite shells. The use of three-dimensional finite elements for predicting the delamination of these structures is computationally expensive. Here combined double-layer and single-layer of shell elements are employed to study the effect of delamination on the strain values in the sample under purely bending loads. The computational load and the accuracy of the modeling approaches are compared. It is shown that through-the-thickness delamination can be modeled and analyzed effectively without requiring a great deal of computing time and memory. Some of the results are compared with the experimental results.

Modeling of delamination in composite shells under different temperature conditions

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