Dynamic model of an electromechanical de-icing system coupling fracture and resonance

Abstract Preventing ice accumulation on aircraft surfaces is a real challenge in industrial aviation. Notably, ice buildup significantly impacts the functionality of wings and control surfaces, thereby diminishing overall aircraft performance. Existing in-flight ice protection solutions, such as the use of hot air from engines or electrical resistance for surface heating, as well as the use of inflatable pneumatic boots, are characterized by either high energy consumption or maintenance requirements. Moreover, it is anticipated that the aerospace sector will undergo a substantial transition toward electric technology in the coming decade. In response to this shift, ongoing research and development efforts explore electromechanical systems to mitigate ice accumulation. This study concerns resonant electromechanical systems that reduce the power required for de-icing by exploiting the phenomenon of resonance, which naturally amplifies the vibrations used to break up and expel ice, but whose frequency varies with ice shedding, which makes it difficult to control. The formulation of a representative dynamic model of the actuation system and the ice fracture mechanism would enable control laws to be developed to operate the de-icing system at its optimum operating point, even if the latter is variable. Consequently, this study aims to develop a numerical model capable of accurately simulating the dynamics of resonant electromechanical de-icing systems. At the end of the study, this model will be used to tune the excitation signal controlling the de-icing system in open-loop.