Repair of composite laminates-II: Models

Models were developed for calculating the failure loads of composite laminates repaired by scarf and uniform lap techniques. The models take into account anisotropy of each ply in the laminate and in the repair ply and non-elastic behavior of the adhesive or resin interlayer between the laminate and the repair patch. On the basis of the models two computer codes were written for generating numerical values of the failure loads. The first code is for calculating the failure loads of laminates repaired by the uniform lap technique, the second for calculating the failure loads of laminates repaired by the scarf technique. Failure loads calculated by the models, and the corresponding computer codes, were compared with data, and good agreements were found between the results of the models and the tests.