Mathematical modeling and ground tests of a fuel cell hybrid unmanned aerial vehicle in cruise phase

With the recent developments in battery and electric motor technologies, the areas of use of Unmanned Aerial Vehicles (UAVs) have expanded significantly and UAVs have become a part of civilian life. Initially used for military purposes and with long ranges with combustion engines, UAVs have focused on electric motors over time due to the environmental damage caused by fossil fuels. Electric motors are widely preferred in the civilian UAV sector due to their low emission advantages, simple operation features and low operating costs. However, the low energy density of the batteries that meet the energy needs of electric motors keeps the range of electric UAVs shorter compared to internal combustion engines. In order to increase flight times and ranges, scientists have been working on various hybrid systems and some promising results have been obtained. Inspired by these successful results, this thesis aims to develop a hybrid propulsion system architecture that can increase the range of electric UAVs. The studies in the literature have been examined in detail and it has been observed that they contain complex system architectures. In this context, this thesis aims to create a simple and accessible architecture. Components suitable for the architecture were selected and the hybrid system's operating performance was observed by performing static power tests. In addition, static power tests were performed with the power profile of the flight profile created for a fuel cell UAV and the results were evaluated.