Modelling of an ice protection system based on icephobic and piezoelectric technologies, for WT demonstration.

Inhalt:
Icing represents a serious problem for the aeronautic sector for its impact on the aerodynamic efficiency, the engine life and the authority of the aerodynamic surfaces. Conventional ice protection systems assure a safe and adequate protection, but present some drawbacks: they are power consuming and invasive. Moreover, with the emergence of new aircraft concepts, based on electrical propulsion or with a large use of electrical power, classical Ice Protection Systems (IPSs), based on hot-air spilled from engine, cannot be used. For this reason, attention is paid to novel approaches. This work focuses on the design of an innovative IPS based on piezo-electrics and superhydrophobic (SHC) coating, applied to a wing section demonstrator that will be tested in the ice wind tunnel facility of Fraunhofer IFAM. The paper starts with an overview on similar applications. Then the requirements of the proposed concept are critically discussed and, on this basis, the layout of the system is sketched. A dedicated numerical model, that was realized in order to adequately describe the action of the piezoelectric transducers, in charge of driving mechanical waves to detach the ice, is described. The work ends with an overview of the results achieved, expressed in terms of percentage of the amount of ice detached at the interface with the skin element.