Parametric instability due to longitudinal forces is becoming a critical issue for lightweight and flexible modern day aerospace vehicles. An attempt is made in the present work to develop a FE model for a piezoelectric actuated laminated composite shell panel subjected to parametric edge excitation. A feedback control strategy is developed with the piezo sensor output being fed back to the IDE-PFC actuators. Employing Hamiltonian principle, governing differential equation taking the form of Mathieu-Hill equation is developed. The resulting equation is solved using the method of strained parameter. Results for various geometries, boundary conditions and lamination sequences are obtained and discussed.