In this paper, dynamic analysis of a composite wing of a typical airplane with Piezoelectric sensor and actuator patches has been performed using ABAQUS finite element package. The modal analysis for a 3-D model of a specified wing made up of three different composite material including basalt-epoxy, kevlar-epoxy and carbon epoxy has been done to determine and compare modal shapes of the composite wing and its corresponding natural frequencies. Then, based on structural analysis, 3-D distributions of stress, strains and displacements components are obtained. Moreover, using a written code in MATLAB/Simulink applying the PID controller to the model, the vibration control of the composite wing has been investigated, to do this, the responses of both open and closed loop control models of the system with PID controller under external disturbance forces in the form of either unit step, ramped and sinousuidal input functions are extracted. It was shown from the obtained results that the composite wing made up of carbon-epoxy material has modal natural frequencies higher than that of aluminum wing. Also, considering the closed loop PID controller for the composite wing with Piezoelectric actuators revealed that a very good performance of the system against applied disturbances in which the active PID controller reduced the wing tip displacement under disturbances in the form of unit step, ramped and sinousuidal functions by 96.5%, 98% and 99%, respectively.