This thesis presents the development of an ice protection system model for a hybrid propulsion regional aircraft which could take advantage of the higher electrical energy stored on-board this kind of aircraft. In regions where aircraft frequently encounter high concentrations of super-cooled water in clouds and low temperatures, the risk of ice formation on external surfaces is substantial, causing negative effects on aerodynamic performance and potential loss of control on the aircraft. To mitigate the associated flight problems, ice prevention systems are crucial. Therefore, the present study starts with the definition of the characteristics of the icing phenomena and how they affect the behaviour of aircraft during their operation.