Nonlinear multibay panel flutter evaluation of composite laminates with curvilinear fibers.

Resumo

© 2020, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.Panel flutter is a real design issue for supersonic flying aerospace vehicles caused by flexible panels subject to unsteady supersonic aerodynamics loading that can lead to critical fatigue damages and catastrophic failures. Many efforts earlier were devoted to this problem, considering the numerical evaluation of a single panel solution typically. Rather than this approach, it is proposed in this paper the nonlinear aeroelastic analysis of adjacent panels, the so-called multibay panels, within the context of variable stiffness composites laminates (VSCL). The aeroelastic model is based on coupling the first-order piston theory with the VSCL structural model developed in accordance with the Classical Lamination Theory (CLT) using the von Kármán’s assumptions to account for geometrical structural nonlinearities. Moreover, the Newmark numerical time-integration is used, aiming to improve computational efficiency. The results of numerical solutions considering four different scenarios are presented, enabling the aeroelastic performance comparison with a conventional laminate, taking into account different fiber trajectories with and without ply contiguity between panels.