Aerothermoelastic analysis and active flutter control of supersonic composite laminated cylindrical shells

The aerothermoelastic characteristics of the supersonic laminated cylindrical shell are analyzed, and the active flutter control of the aeroelastic structure is also investigated using the piezoelectric material. In the structural modeling, the influences of the in-plane thermal load on the transverse deformation are taken into account. The aerodynamic pressure is evaluated using the supersonic piston theory. Hamilton’s principle and the Galerkin’s method are used to establish the equation of motion. The proportional feedback and LQG control methods are applied to design the controller. The aerothermoelastic analysis for the laminated cylindrical shell is carried out using the frequency- and time-domain methods. The influences of the ply angle on the flutter and thermal buckling properties are investigated. The active flutter control effects of different controllers are compared. Numerical simulation shows that the LQG controller is more accurate and effective than the LQR and proportional feedback controllers.