科研之友
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摘要
Aerothermoelastic characteristics of composite laminated panels with time-dependent boundary conditions are investigated. The macro fiber composite (MFC) which is more adaptive and effective than the traditional monolithic piezoelectric materials is applied to control the structural vibration. The MFC actuator and sensor are bonded on the top and bottom surfaces of the panel so that the active flutter control can be conducted. Aerodynamic pressure is evaluated by the supersonic piston theory. The governing equation of the electromechanical and thermal coupling system is established by the extended Hamilton's principle with the assumed modes method. By solving the eigenvalue problem, natural frequencies of the structural system are obtained. Frequency- and time-domain responses are computed to analyze the aerothermoelastic properties of the laminated panel. The influences of ply angle and aspect ratio of the laminated panel on the flutter behaviors are investigated. The displacement feedback control (DFC) and linear quadratic Gaussion (LQG) methods are performed to design the controllers. The active control effects under the two different controllers are compared. It is observed that both the DFC and LQG methods can suppress the vibration, and the LQG is more effective than the DFC controller in flutter suppression of the laminated panel with time-dependent boundary conditions.
