Numerical aeroelastic flutter prediction of variable stiffness laminated panels with curvilinear fiber in supersonic flow

Abstract

The flutter behaviour of layered structure has been investigated in this research considering the curved fibre instead of the conventional type of fibre directions (uni/multiple directional types). Due to the change in angles, the influences of fibre directions on the final properties of the laminated structure results in variable stiffness. The effective properties of composite in conjunction with the aeroelastic loading under the supersonic flow have been computed numerically. The numerical responses are calculated through an in-house MATLAB code prepared from the higher-order displacement polynomial and isoparametric finite element formulation. The aeroelastic loading effect is incorporated via the standard first-order Piston theory. The necessary comparison and convergence tests are performed to show the model's accuracy. Further, the influential parameters (geometry and material) with and without fibre directional effects are examined and discussed in detail.