Effects of Piezo Actuated Damping on Parametrically Excited Laminated Composite Plates

The present day aerospace vehicles are becoming lighter and more flexible and are subjected to different kinds of longitudinal forces, namely thermal and pulsating inertial loads. While designing such structures, parametric instability plays a very important role. In the present work, a study is undertaken to understand the parametric instability behavior of laminated composite plates integrated with active piezoelectric layers used for feedback damping. An eight-noded isoparametric finite element model has been developed with structural and electrical degrees as degree of freedom and coded in FORTRAN to obtain the stiffness, mass, and the feedback damping matrices. The resulting Mathieu—Hill equation is then solved using the strained parameter method. Results for different geometry and fiber orientation are obtained and presented.