Abstract
A method is presented to build reduced (equivalent) models of thin-walled composite structures to be used in the modal analysis of composite aircraft wings. The technique is developed to allow finite element modeling and analysis using a single-type, three-dimensional orthotropicp element. The use of a single element guarantees speed and flexibility in the (re)modeling of the structure and reduces the modeling and analysis errors connected to finite element analysis in prdiminan-desisil/imiltidiscliplinary-optimization environments. The method is tested on a sandwich plate. The dynamic behavior of sandwich plates is determined by the in-plane extensional and shear stiffness of the facings just as the behavior of the wing box is determined by the extensional and shear stiffness of skin panels and spars. Numerical results obtained with solid orthotropicp elements show the validity of the method. Comparison with results from traditional linear shell finite elements models shows that with the new method more accurate results can be obtained with fewer degrees of freedom.
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