The surface protection systems of aerospace and aircraft structures are lately more often constructed from discretely stiffened composite panels. Composite materials proved to be suitable for those structural applications. This paper presents an analytical study on dynamic response and structure-borne sound transmission of these structures due to random loading conditions. A generalized transfer matrix procedure for composite-stiffened flat panels is developed to obtain the required dynamic response solution. Modal decomposition is used to predict the interior noise transmission. The acoustic enclosure is taken to be rectangular in shape. A portion of the boundaries is elastic (composite material), whereas the remaining surface is acoustically rigid. Numerical results are presented for acousto-structural applications.
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Lyrintzis et al. (1990) studied this question.
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