کنترل غیر خطی فلاتر با استفاده از پیزوالکتریک و در نظر گرفتن سطح مقطع شکل ایرفویل بال

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 sys-tem is controlled here using piezoelectric actuator and nonlinear feedback controller of Feed-back Linearization (FL) approach. Fluttering of the plane wing has a significant destructive effect on the plane manoeuvre. In order to compensate this phenomenon a proper actuator needs to be employed together with an appropriate controlling strategy. Piezoelectric is pro-posed 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.