FE Analyses of Aircraft Model with Interior Trim

摘要

A finite element (FE) analysis of the dynamic behavior of an aircraft fuselagewith interior trim panels was performed. The FE model used is a half model of the fuselage shell, the trim panels, the acoustic cavity in between the two shells, and the interior acoustic cavity. For the present model, the eigenvalues and eigenmodes between 50 and 100 Hz are shown and observations regarding fluid structure interactions are made. The influence of the trim acoustic cavity is demonstrated through both a substantial resonance frequency shifting and an increased transmission.