DYNAMIC BUCKLING INVESTIGATION OF AIRCRAFT COMPOSITE STANCHIONS SUBJECTED TO CYCLIC LOADING CONDITIONS

This work is focused on the investigation of the structural behavior of a composite floor beam, located in the cargo area of a civil aircraft, subjected to cyclical low frequencies compressive loads. In a first stage, the numerical models, able to correctly simulate the investigated phenomenon, have been defined. Different analyses have been performed, aimed to an exhaustive evaluation of the structural behavior of the test article. In particular, implicit and explicit analyses have been considered to preliminary assess the capabilities of the FE code. Then, explicit non-linear analysis under dynamic loads have been considered, to predict the behavior of the composite structure under cyclic loading conditions.