Abstract

Electrothermal de-icing systems are highly reliable and controllable, offering significant potential for aircraft light-weighting and low-energy flight. In order to achieve rapid de-icing, it is important to design the energy distribution system of the aircraft rationally. In this paper, an energy distribution optimization method for aircraft electrothermal de-icing is established based on genetic algorithms. Heating elements are placed at the leading edge of the aircraft, with the total power and power density range of each heating element as constraints. The shortest time to phase transition of a 0.2 mm ice layer into a water layer is set as the optimization objective. The optimization results show that the power distribution of the heating elements changes with the thickness of ice layer, and the corresponding phase transition of the optimal distribution scheme is more pronounced in the area in contact with the air compared to the internal area.