Abstract
Results from an analytical and experimental study of the dynamic response of an aircraft fuselage panel are presented. The ability to predict the dynamic response of a complex stiffened panel into the kilohertz region using finite-element methods is examined. Beam and plate element models of the stiffeners are evaluated with numerous mechanisms for attaching the stiffeners to the plate elements representing the panel skin. The analytical models are validated with an extensive database of Scanning Laser Doppler Vibrometer (SLDV) data acquired by the Naval Research Laboratory and Electro-Optic Holography (EOH) measurements. For both measurement techniques, forced response data were acquired with soft springs supporting the panel to simulate free–free boundary conditions. The analytical results were obtained from a normal mode analysis of the various panel finite element models with free–free boundary conditions. The finite element models are described and comparisons between the analytical and experimental results are presented.
Published Version
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