Simulação da propulsão aeronáutica híbrido-elétrica

Abstract

The present work aims to describe an example of a hybrid-electric propulsion system for aircraft, as well as its components and forms of interaction, to energetically model this system and simulate its behavior with computational tools applying an exergoeconomic analysis. Combining two power sources, the aircraft's specific advantages and behaviors are achieved, presenting particularities when compared to the conventional propulsion system. A model is proposed, based on the bibliography and a computer simulation, so that some of these behaviors and characteristics will be presented and studied to aid in the operational control decisions of the air vehicle, aiming at a better energy management and a better efficiency in flight missions. With the aid of the system of equations that correspond to the states of the components and their interactions, some simplifying hypotheses were used, demonstrating the main characteristics of the components and the factors that most influence the energy management of an aerial vehicle. From an exergetic point of view, thermodynamic conditions and operational parameters will be analyzed, helping control decisions aiming at a better energy management of the aircraft. Having characterized the problem, for the entry conditions, it is noticed that the battery is identified as the main contributor to the mass of the propulsion system. As well as the great influence of the lower calorific value of the fuel, both of which are the focus of future improvements. The greatest overall energy efficiency of the aircraft is given when the propulsion is given 87% by the battery.