Abstract
This work investigates the aeroelastic stability boundary of curved composite panels with embedded Macro Fiber Composite (MFC) actuators in the supersonic airflow. Prescribed voltages are statically applied to the MFC actuators, inducing a pre-stress field which results in an additional stiffness effect on the curved panels, thus changing the aeroelastic stability boundary of curved composite panels. The principle of virtual work is applied to develop the equations of motion for the nonlinear flutter of curved composite panels with embedded MFC actuators. The Von Karman large deflection panel theory and the first order quasi-steady piston theory are adopted in the formulation. The Newton-Raphson method is employed to determine the static aeroelastic deflection under the applied voltages, and an eigenvalue solution is adopted to predict the aeroelastic stability boundary of the curved panels. Numerical results show that the influence of the applied voltages is distinct for the curved composite panels with different curvatures. In addition, the lamination angles of the MFC actuator and the temperature elevations will also significantly affect the aeroelastic stability boundary of curved composite panels in the supersonic airflow.
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