Utilizing piezoelectric actuators to micro-vibration generation for de-icing system of aircraft

To improve aviation safety as well as reduce environmental and cost dangers related to airplane icing, reliable, sensitive, and aerodynamically compatible de-icing techniques are in great demand. This paper proposed a vibration de-icing method for aircraft wings with piezoelectric actuators. The effect of position, thickness, and voltage applied to the piezoelectric actuators on natural frequencies and shear stress generated at the interface of the ice with the aircraft wing are examined utilizing the finite element method via ABAQUS software. Consequently, if the proper characteristics of piezoelectric actuators are determined, adequate shear stress can be generated to overcome the adhesion of ice layers to the airfoil surface. The results of DOE demonstrate that three piezoelectric actuators with a length of 300 mm and V = 50 V hold the best performance, and the maximum shear stress created in this case equals 29 MPa.