Simulation of an electro-mechanical ice protection system for aircraft structure based on ultrasonic guided wave

The benefits of greater fuel savings and lesser environmental effects (i.e. better efficiency and lower emission) through the use of avant-garde open rotor propeller unfolded the next technology for the imminent generation of single-aisle aircraft. However, ice accretion on aircraft during in-flight significantly affects the aerodynamic performance and control of the plane due to the increment of drag and imbalance caused by the non-uniform mass of ice. This continues to be a concern as it is widely known to be causing safety incidents. Thus, in order for the open rotor propeller technology to take forward with improved aviation safety, method must be found to enable power efficient de-icing system in particular targeting the leading edge of the open rotor blade which is prone to ice accretion. In this paper, we investigate the use of an electro-mechanical technique involving piezoelectric actuators to excite shear stresses on the Carbon-Fibre-Reinforced Polymer (CFRP) blade structure which potentially led to the de-bonding of ice from the surface. Essentially, this Ultrasonic Guided Wave (UGW) Ice Protection System (IPS) is subject to Finite Element Method (FEM) analysis to study the wave propagation through the CFRP blade and ice configurations. The optimum excitation of the actuator is then determined by the generated shear stress which exceeds the adhesive shear strength for ice and composite. The developed computational model of UGW based IPS allows the excitation parameters to be optimised for de-icing of various ice conditions. The optimum parameters will form the basis of instrumentation for the experimental trial to be underway.