• shear buckling
• composite laminate
• analytical approximation

The aim of this work of thesis is the development of a procedure which harmonize existing methodology, employed in a manufacturing contest, for evaluation of buckling onset on laminate composite at panels subjected to shear loads, by means of non-dimensional approach. A comparison between numerical and parametric results highlights the substantial effectiveness of the FE method in predicting the structural response of the subcomponents in terms of buckling onset and of their post-buckling behaviour in load ranges suitable to composite airframe. A detailed description of parametric analysis and approximated solution is provided. Finally, a through comparison of the model results with the experimental data is presented and commented. The experimental data for model validation were collected during a test campaign on the materials selected. Due to their strictly closed-form analytical nature, the presented approximated methods can be used conveniently in engineering practice for all application purposes where computational time is a crucial factor, especially for preliminary analysis and design or optimization procedures.