Investigation of various electric drive systems for various aircraft load scenarios

Kurzfassung

Electric aircraft are being extensively researched nowadays. One of the most important components in their structure is electric drive, parts of which must be selected and then its behaviour must be controlled. In this master’s thesis, an electric drive was selected, modelled and a control design for its regulation was developed in Matlab/Simulink using optimal control algorithms. In addition, the created control topologies were tested under various aircraft load scenarios in order to evaluate the performance of the system and see how the electric drive behaves in different situations. Finally, the results show the most suitable control algorithm and a possible implementation of the topology.