Flutter analysis of a sandwich composite beam using an analytical method

Abstract

In this paper, the aeroelastic behavior of a composite wing is investigated in the compressible flow using the analytical method. The composite wing is simulated as a thin-walled single-cell closed cross-section beam with circumferentially asymmetric stiffness (CAS) configuration. The best layup configuration for the maximum flutter speed is determined by analyzing four layups configuration where the fiber orientation angle varies within the range of 0–90 degrees. Moreover, an included foam layer between composite layers resulted in higher bending stiffness and improved stability characteristics of the wing. It was shown that there is a significant improvement in the flutter speed for [Formula: see text] layup. Numerical results demonstrate the advantages of foam filled model over the model without foam in terms of the flutter speed to the weight ratio.