Mathematical modelling and experimental verification for the electrical propulsion system of a micro / mini class unmanned aerial vehicle

When looking at the world aviation activities, the works on unmanned aerial vehicles seem like a very interesting topic. The aviation activities in our country have started to accelerate in the mid-1990s. Within the UAV activities works on the thrust systems, and in the private sector, the electrical thrust systems hold a very important place. When we look at the aviation industry of our country, the calculation and analysis of thrust systems in the design of UAVs are largely professionally outsourced. In this regard, for this thesis study a thrust system design for a micro/mini-class UAV was made and the mathematical model of this design was established. This model was then largely transferred to the MATLAB/Simulink program and by selecting the appropriate components and performing simulations within the framework of certain parameter values and a MATLAB/Simulink model was created. After that an experimental setup system including all these thrust system components and measurement instrumentation was installed. Tests were made for 5 different PWM values for both non-propeller and propeller conditions. All these test results were evaluated first and then simulated with the MATLAB/Simulink program and ultimately all these results were compared and analyzed. The results obtained at the end of the study show that the simulation and test results overlap to a great extent.