Abstract Piezoelectric actuators are widely used in several applications and are becoming increasingly attractive in aircraft and industrial contexts, mainly when efficiency and economical energy conversion are required. One of these applications is the avionic piezoelectric deicing system. Piezoelectric actuators are considered as a potential solution for developing a low-energy ice protection system for aircraft. This type of system applies vibration to the structure by activating its own resonant frequencies to generate sufficient stress to break the ice and cause it to delaminate from the substrate. The deicing mechanism depends strongly on the chosen excitation mode, whether it is flexural (bending) mode, extension (stretching) mode, or a combination in between, hence affecting the efficiency and effectiveness of the deicing process. In this contribution, a proof of concept of a deicing system utilizing lightweight piezoelectric actuators with minimal power requirement is proposed. Deicing was demonstrated with a power input density of 0.074 W cm −2 and a surface ratio of 0.07 piezoelectric actuators per cm 2 . First, a numerical method for positioning piezoelectric actuators and choosing the proper resonance mode was validated to assist in the system’s design. Then, the numerical method was used to implement piezoelectric deicing on a more representative structure of an aircraft wing or nacelle. Finally, a converter topology adapted for deicing application was proposed.