Refined models for the limit-cycle oscillation prediction of VAT composite panels in supersonic flow

摘要

Panel flutter is an aeroelastic phenomenon that appears at supersonic regimes. Panel flutter does not always lead to a catastrophic failure, but a limit-cycle oscillation (LCO) usually appears. This phenomenon creates severe mechanical stresses in the components that may results in early failure due to fatigue phenomena. The present paper presents a refined kinematic finite element model for the prediction of the LCO in variable angle tow composite structures exposed to supersonic flows. The Carrera Unified Formulation has been used to derive a class of refined one-dimensional elements able to deal with advanced materials. A classical aerodynamic model, the piston theory, has been used to describe the flow field.