Abstract
The possibility of realizing full electric or hybrid electric propulsion for aircraft has been considered due to the constant growth in the use of electric technologies in aircraft and the availability of high-power-density electrical machines and converters. In this paper, an optimized design approach is proposed with reference to the optimal trade-off between energy storage system sizing and the fuel mass of a series of hybrid aircraft. The problem is approached using an integer optimization algorithm based on differential evolution and by mixing both the flight mechanics and the electrical issues inherent to hybrid flights. This method has been validated by means of implementing numerical simulations and the results are reported and discussed in the paper.
Highlights
In the last two decades, increasing interest regarding the More Electric Aircraft (MEA) concept has been generated [1] with the aim of reducing fuel consumption, reducing emissions released into the atmosphere, increasing the redundancy and the reliability of onboard power systems, and reducing aircraft noise.Recently, several research projects have led to the substantial electrification of onboard pneumatic components in order to increase the efficiency of flight systems—which has introduced redundancies across the subsystems [2]—and the necessity to propose new power system architectures for the reduction of weight, increase of the reliability and to assure the correct performance of electrical drives [3]
In the all-electric propulsion concept, the fuel and the thermal engine are completely substituted with energy storage systems that are able to provide the entirety of the electric power required by the aircraft
The performance of the proposed optimization procedure is verified by means of numerical simulations implemented in Matlab ©
Summary
In the last two decades, increasing interest regarding the More Electric Aircraft (MEA) concept has been generated [1] with the aim of reducing fuel consumption, reducing emissions released into the atmosphere, increasing the redundancy and the reliability of onboard power systems, and reducing aircraft noise.Recently, several research projects have led to the substantial electrification of onboard pneumatic components in order to increase the efficiency of flight systems—which has introduced redundancies across the subsystems [2]—and the necessity to propose new power system architectures for the reduction of weight, increase of the reliability and to assure the correct performance of electrical drives [3]. In the last two decades, increasing interest regarding the More Electric Aircraft (MEA) concept has been generated [1] with the aim of reducing fuel consumption, reducing emissions released into the atmosphere, increasing the redundancy and the reliability of onboard power systems, and reducing aircraft noise. In the all-electric propulsion concept, the fuel and the thermal engine are completely substituted with energy storage systems (above all, fuel cells and battery) that are able to provide the entirety of the electric power required by the aircraft. The use of these new energy systems on board aircraft has been analyzed widely in the literature. Tariq [11] presents an overview of the battery systems for the MEA with an analysis of battery management systems for Li-ion batteries
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