Abstract
A finite element - decaying wave method is used to determine the frequency response of various simplified fuselage structures. The structures examined in this work are flat, damped, periodic panel-stringer-frame configurations, of various widths and lengths, under hinged boundary conditions. Where possible, results from response plots are compared with those in the literature, and trends concerning the frequency response of multiple-row structures are shown. The solution method used is a combination of a finite element - transfer matrix method and a wave propagation approach, which gives it certain advantages over a standard finite element or transfer matrix technique.
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