Abstract:
This title describes the development of a mathematical control system for a small fixed-wing aircraft with unconventional aerodynamic surfaces. The research process involved an analysis of the complex factors influencing the dynamics of aircraft, represented by a set of differential equations. The study focused on identifying and selecting the parameters necessary for creating a mathematical model of a non-standard control system. This system is designed to generate and deliver commands to actuators responsible for the aerodynamic surfaces, which are arranged in a unique configuration. The developed mathematical model incorporates the control of innovative, domestically produced brushless electric motors, taking into account their specific technological characteristics. The efficiency of the mathematical model was validated in the MATLAB software environment using the Simulink toolbox, considering various operational conditions. The culmination of the work was the experimental testing of the control system and the mathematical model on a physical prototype, enabling the control of unmanned aerial vehicles with innovative, non-standard aerodynamic configurations.
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