FE model and experimental test bench for vibration analysis in aeronautic composite structures

Structural Health Monitoring(SHM) systems are developed withdifferent techniques to assess non detectable damage inside CFRP materials. In order to certify the air worthiness of the system, the SHM equipment must becompliant with RTCA standards in terms of vibration.In the present work,a test setup for vibration certification of electronic components mounted on CFRPl aminaplates is presented.The proposed system reconstructs the boundary conditions of a fuselage compositeplate, to be equipped with the SHM system.The experimental testbench is realized and vibration data are obtained from the panel via MEMS accelerometers.From these results,a dynamic implicit FE model is developed to assess the effects of vibrations on theSHM system.Further developments involve tuning of the model physical constants,concerning in particular the material stiffness and damping,to improve the correspondence with the actual results.