Abstract
This study addresses the preliminary design of a fixed-wing, tailsitter electric unmanned aerial vehicle (with vertical take-off and landing capability) by optimising the size of the powertrain components together with the main aircraft design specification. To this scope, different optimisation problems are considered, with two, three and four objective functions, respectively. The results of the optimisation are used not only to compare the performance of different optimisation algorithms when increasing the number of goals, but also to discuss the synergy between architecture and power systems optimisation.
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