ICNPAA 2010: Mathematical Problems in
Engineering, Aerospace and Sciences

Frequency response analysis of an aircraft shell panel subject to geometrical imperfections and material properties using a probabilistic approach was evaluated. A stochastic finite element model was developed and implemented applying the Monte Carlo method to perform several spectral distributions and obtaining non-deterministic results. This work extends previous results obtained with the buckling instability analysis for an aircraft plate panel. In this research, the investigation considers the variations for shell panel geometry and material properties. In order to observe the major contributors, a sensitivity analysis was performed. The modal results and the frequency response function variations are presented.