Abstract
This work focuses on the layerwise finite element modelling and active aeroelastic flutter control of smart variable stiffness laminated composite panels with surface bonded piezoelectric layers/patches under supersonic airflow. The proposed aero-electro-elastic models make use of the First- and Third-order Shear Deformation Theories, along with a linear through-thickness distribution of the electric potential, whereas the effect of the supersonic airflow is described by the First-order Piston Theory. Numerical applications of simply supported smart composite panels with either curvilinear or unidirectional fibres are provided for the accuracy assessment of the proposed models predictive capabilities, considering various side-to-thickness ratios and control conditions. The effect of proportional control on the aeroelastic flutter response is discussed for both airflow along the x-axis and yawed airflow, in addition to three different placement configurations of the piezoelectric patches.
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