NUMERICAL AND EXPERIMENTAL ANALYSIS OF AERONAUTICAL CFRP COMPONENTS SUBJECTED TO STRUCTURAL LOADS

In this work, numerical models and experimental tests are performed to validate analysis methods applied on aeronautical CFRP components. In particular, tests of a multi-stingers panel under static compression load and a repaired spar under dynamic bending load are reported. The FEM model are realized to reproduce the panel’s geometry and stacking sequence, the constraints and representative loads of the component's service. Numerical models are improved to reduce the differences between the calculated and experimental deformations, allowing the experimental test validation. In the multi-stringer panel, the experiences evaluate the effects of the out-plane deformations due to compression failure, the difficulties of alignment and distribution’s load along and finally the validation of the numerical model. While in the spar’s study, the experimental measurements confirmed the predictions of the numerical model.