Análise termoeconômica da propulsão híbrido-elétrica em aeronaves (estudo de caso).

Abstract

With the recent technological advances, the new means of energy production started to be created, being one of them the hybrid electric propulsion system. One of the reasons for creating this system is that it causes two or more different energy sources to work together, bringing together the advantages of each. With this, new challenges arise for the creation of this system as the management of these energies coming from two or more distinct sources and the knowledge and control of the associated final exergetic cost. In this work, we proceed to a study of thermoeconomic analysis and energy management of hybrid electric propulsion in aircraft. A preliminary mathematical model that describes the operation of the fuel tank and the battery in transiente regime, the internal combustion engine, the converters, the electric motor and the propeller in permanent regime, such as the balances of mass, energy, entropy, and exergy applied to these components. A computer simulation was performed in a simultaneous equation solution software, where it is evaluated or hybridization factor for better overall efficiency, or lower final aircraft weight, higher overall exergetic efficiency and lower exergetic cost. The present study was based on the experiment bench created by the electromechanical energy conversion group (GCEME). For the entry conditions, it was verified that the hybrid system can supply the same demands as a conventional system with advantages of higher overall and exergetic efficiency when a propulsion is given 90% by battery, lower final takeoff weight when a propulsion is given 20% by battery and exergetic cost 75% lower than conventional system when propulsion is given 50% by battery.