In the master thesis, we investigated the use of hydrogen in aviation, specifically the application of fuel cells and hydrogen storage in aerobatic aircraft. Based on the data obtained for the fuel cell stack and other auxiliary components, a simple numerical model was built to calculate the mass and energy fluxes. We considered the initial requirement of at least 300 kW of power at the electric motor shaft and a flight duration of 5 min. Using a 3D modeler, all the components required to convert the airplane were fitted into the frame. The dimensions and masses of the intended components are taken from the specifications of commercially available products. Based on the model, the final mass was estimated and the center of gravity of the system was determined. Finally, suggestions for possible improvements are given.
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