Abstract
In a previous work, the authors optimized the hybrid electric power system for a tactical Unmanned Aerial Vehicle including a Wankel engine as thermal converter and a permanent magnet electric motor powered by lithium batteries. Startingfrom this optimal configuration, we address here the topic of a refined optimization of the energy management strategy, i.e. the contribution of the battery to the required power in each segment of the flight. The Equivalent Consumption Minimization Strategy (ECMS) was chosen with the goal of minimizing fuel consumption while fully depleting the energy stored in the battery from the beginning to the end of each mission.
Highlights
In the last decade concepts of power systems electrification have earned an increasing interest due to their several benefits with respect to the conventional configurations, such as higher power-to-weight ratio, reliability, compactness, quietness and, above all, pollutant emissions cutback ([1],[2])
In this framework, advanced genetic algorithms were found in previous studies to be a precious tool, because they allow taking into account several metrics or optimization goals and a large number of input parameters [5] including aircraft specification, flight conditions, architecture, size of converters and storage systems, energy management strategies and so on
The authors performed the optimization of the preliminary design and energy management of a parallel hybrid electric power system for a tactical Unmanned Aerial Vehicle
Summary
In the last decade concepts of power systems electrification have earned an increasing interest due to their several benefits with respect to the conventional configurations, such as higher power-to-weight ratio, reliability, compactness, quietness and, above all, pollutant emissions cutback ([1],[2]). In this framework, advanced genetic algorithms were found in previous studies to be a precious tool, because they allow taking into account several metrics or optimization goals (like fuel economy, electric endurance, performance indexes) and a large number of input parameters [5] including aircraft specification, flight conditions, architecture, size of converters and storage systems, energy management strategies and so on. The proposed hybridisation scheme takes advantage from the reduction of the engine nominal power (downsizing).
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