active vibration control and improving flutter characteristics of uav wing by using piezoelectric material

In this research designing the damper and control of system vibrations with the piezoelectric layers accommodation in studying the flutter phenomenon will be considered. accordingly, system structural modeling will be done in a continuous model of unmanned airplane wing. by considering all parameter of the wing, the regions which have piezoelectric layers are modeled as beam with degree of torsion and bending freedom. also, modeling the airflow behavior as quasi-steady will be done. by considering linear theory for piezoelectric structural equations, two layers will be bonded on the top and bottom of the beam. due to design the damper and control of the vibration, negative feedback control (nfc) algorithm will be used. to perform this algorithm, the lower piezoelectric layer acts as sensor. in fact, it has to measure the harvesting voltage. on the other hand, the upper piezoelectric layer, is the actuator of the system. in the other words, with feedback of measured voltage of the sensor to the controller, it applies new voltage to the system to control the stability of the system and at the end the flutter phenomenon can be postponed by using this algorithm. the results will presented for different values of feedback coefficient. additionally, the effect of system main parameters on postponing flutter in each case of algorithm will investigated and optimized value of each parameter will showed based on postponing flutter phenomena.