Nonlinear Control of Wing Fluttering Using Piezoelec-tric and Considering the Airfoil Shape Cross Sectional Area of the Wing

The fluttering model of an airplane wing is modelled in this paper as nonlinear system with its real cross-sectional area which has an airfoil shape. Also, the fluttering of this nonlinear system is controlled here using piezoelectric actuator and nonlinear feedback controller of Feedback Linearization (FL) approach. Fluttering of the plane wing has a significant destruc-tive effect on the plane manoeuvre. In order to compensate this phenomenon a proper actua-tor needs to be employed together with an appropriate controlling strategy. Piezoelectric is proposed here for implementing the required tension on the wing surface since its dynamic is controllable using voltage input with a fast time constant. Also, in order to calculate the re-quired feedback-based voltage of the piezoelectric, the real nonlinear model of the wing flut-tering is required to be employed as the related feedforward term. To meet this goal the non-linear model of the wing beam together with its related piezoelectric is extracted here as a nonlinear system with its real cross-sectional area which has an airfoil shape. It is shown by the aid of some simulation scenarios that first of all the developed model is closer to the reali-ty of fluttering phenomenon. Also, the designed and implemented nonlinear controller of FL can successfully damped away the wing vibrations and increase the fluttering speed.

کلیدواژه ها:

Fluttering model ، Airfoil shape cross sectional area of wing ، Feedback lineariza-tion ، Piezoelectric.