Abstract
The electroimpulse de-icing system of an aircraft wing leading edge is investigated through the development of a methodology for the numerical simulation of the electroimpulse de-icing process. The principle of electroimpulse de-icing is that the ice is removed due to the leading edge local mechanical vibration, which is induced by an electromagnetic pulse. The numerical simulation methodology is based on a nonlinear transient three-dimensional stress analysis of the ice-covered wing, combined to a de-icing criterion that takes into consideration the tensile and shear stresses at the ice-skin interface. The developed methodology is verified on de-icing experimental tests of an aluminum plate. Afterwards, the methodology is applied to the prediction of de-icing of an aircraft wing leading edge. The dominant process parameters are determined to be the coil number and position, the ice thickness and coverage, the radius of wing curvature, and the electroimpulsive load amplitude. A parametric study is performed to determine the influence of the process parameters on the system effectiveness, defined as the percentage of the de-iced surface over the total leading edge surface. From the results of the parametric study, the possibilities of reducing the weight and energy consumption of the electroimpulse de-icing system can arise.
Published Version
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