Abstract
The frequency response matrix is determined for a periodically supported, periodically damped, closed circular beam structure which is an approximate model of a skin-stringer aircraft fuselage structure. The analytical technique which is developed depends on the periodic nature of the structure to simplify the analysis. The analysis is a complementary approach to the transfer matrix method for determining frequency response. One purpose of the analysis is to circumvent the numerical and/or computer storage difficulties commonly found in computing the frequency response for typical aircraft fuselage structure from a transfer matrix analysis. Numerical difficulty is avoided by using the properties of the transfer matrix for one periodic unit and a consequence of the Cayley-Hamilton theorem to obtain an analytical solution for the frequency response matrix. The second purpose of the analysis is to investigate the spatial decay of response from a point or region of the structure which is being excited. This spatial decay isolates the response to a region of structure near the excitation and reduces the over-all dynamic stress level of the structure for a general excitation. Three damping devices that utilize a viscoelastic link to produce spatial decay are evaluated. Several numerical examples are shown.
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