No abstract

No abstract

This paper focuses on the use of no-contact experimental techniques for monitoring the interlaminar damage evolution in composite laminates. Indeed, Infrared Thermography and Digital Image Correlation are adopted to investigate, in composite plates with artificial delamination, the influence of the delamination initial position on the delamination growth. The paper also investigates the feasibility of using a no-contact experimental technique for the measurement of displacement and strain during mechanical tests, such as the Digital Image Correlation, to evaluate, by means of indirect measurements, the delamination growth as a function of the applied load.

Bird impacts can be extremely critical events for the air transport safety. Since aircraft structures have become more and more complex components, the numerical prediction of the damage onset and evolution induced by a bird impact has become a very challenging task. The aim of this work is to provide a brief overview of the numerical techniques adopted for the prediction of the bird impact phenomenon on a leading edge of a regional aircraft wing. Smooth Particle Hydrodynamics (SPH), Rigid and Lagrangian models have been investigated and the results have been compared and critically assessed.

The present work deals with the Compression After Impact numerical simulations on low velocity impacted glass fibre reinforced composite plates configurations characterised by three different stacking sequences. The damaged numerical FEM models, deriving from impact explicit analyses, have been used as an input to perform explicit analyses simulating the compressive test. The drop, in terms of compressive residual strength, is analysed and discussed. Considerations on the buckling and post-buckling behaviour of these plates under compression are then introduced.