COMPUTATIONAL IMPLEMENTATION OF AN ELECTRICAL ICE PROTECTION SYSTEM IN AIRCRAFT
Erica Konno1; Cláudia De Andrade1; Marcelo Pustelnik2
1 Instituto Tecnológico de Aeronáutica; 2 Embraer
doi:10.20906/CPS/CON-2016-0252
Resumo
Certain weather conditions can influence ice buildups on aircraft surfaces, which can reduce its performance and effectiveness. In order to minimize these effects, ice protection system has been created. Among many systems, electrical systems are being increasingly applied in the aircraft industry. Due to the high energy demand, this system can be used only by aircraft with high capacity of power generation. Studies to feasibility of this method are increasing, and among them, there is the cyclical electro-thermal de-icing system. In this system, the protected region is divided into anti-icing and deicing system, which surfaces are continuous and cyclic heating, respectively. The cyclical electric deicing saves energy because only a small portion is actually ice melted. Most of the ice leaves the surface of the aircraft in solid form. This research aims estimate the power requirement to an electro-thermal cyclical deicing system. The required power calculation method is mainly based on empirical equations and approximation based on thermodynamic and heat transfer equations. The method of cyclic deicing system becomes feasible with two basic principles: reduction of continuously heated area and of heat-on time of intermittently heated areas. A commercial, regional and small aircraft was used for the model application. In order to evaluate the sensitivity of the model, four variables were analyzed: flight altitude, flight Mach, airfoil thickness and heat transfer coefficient. This analysis concluded that the variation of flight Mach and heat transfer coefficient affect only the energy required by continuously heated surface. The variation of airfoil thickness impacts on the same scale in the energy required by the surfaces continuously and intermittently heated and the variation of flight altitude impacts on a larger scale in the energy required by continuously heated surface. In a typical flight profile of the aircraft was obtained the power consumption of 29.337 kW, which 20.463 kW and 8,874 kW equals the por
Palavras-chave: Cyclic deicing system; Ice Protection; Computational implementation of electrical system