The effect of the size of piezoelectric element on shear stress at the interreface of deicing system

For the reason of flight conditions (altitude, high humidity), the helicopter is more susceptible to icing conditions than other fixed-wing aircraft. To meet the requirements of the helicopter flying in all weather, deicing measures must be taken for the blade. There are lots of existing blade deicing methods, electro-thermal is widely used, but the loss of power is very great. With the development of piezoelectric technology, shear vibration deicing is more and more concerned by people for their low power consumption, micro and nano-level vibration and many other advantages. In this paper, the OA212 airfoil helicopter blades are studied, and shear stress between blade and ice is generated by the forced vibration which is driven by piezoelectric ceramic. It achieves the deicing purpose when the shear stress at the interface between the blade and ice is greater than the adhesion stress. In this study, we first study the effect of shear stress for different thickness and length of piezoelectric ceramic, and then analyze the relationship between the shear stress and frequency. Based on the above work, we get the distribution of shear stress on the surface of blade which is driven by a single piezoelectric ceramic.