Nonlinear aeroelastic analysis of a skew reinforced composite panel

Abstract

© 2025 Elsevier LtdThis paper presents a semi-analytical Rayleigh–Ritz model for predicting the nonlinear aeroelastic behavior of skew-reinforced composite panels in supersonic flow until damage arises. The first-order shear deformation theory in conjunction with von Kármán strain nonlinearities is employed for the structural modeling, and quasi-steady first-order piston theory is used for aerodynamic loading. Direct time integration using the central difference method is employed to predict the full nonlinear dynamic response without resorting to modal reduction techniques. A comprehensive parametric study is conducted to assess the influence of various layups, skew angles, and stiffener configurations on the nonlinear aeroelastic response and damage detection. The results provide valuable insights into the flutter-induced damage in composite panels, aiding in the development of a preliminary tool for robust tolerance design. Furthermore, a novel strain energy-based assessment to determine the occurrence of Limit Cycle Oscillations is proposed.

Keywords