Modeling of the Flight Control System of a Hybrid Unmanned Aerial Vehicle in Take-off and Landing Modes

The use of unmanned aerial vehicles for inspection of high-voltage lines meets modern requirements for sustainable development and innovative approach in the energy sector. The article studies the problem of modeling in the Simulink/MATLAB environment of the flight control system of a hybrid convertiplane aircraft in vertical takeoff and landing modes when the aircraft operates according to the aerodynamic scheme of a quadcopter due to the retractable system of rotors. A feature of these modes is the actual change in the geometric and design characteristics of the convertiplane, which requires the use of other aircraft control algorithms. The developed model in Simulink/MATLAB allows evaluating the stabilization and control systems without the need for real tests, which reduces the time and costs of development. Modeling includes analysis of the aircraft dynamics, synthesis of control algorithms and verification of their effectiveness in various conditions. The results demonstrate the possibility of using the proposed model for testing and optimizing the convertiplane control systems in modes where it functions as a quadcopter. This is especially relevant for the preliminary research stage, allowing to minimize risks and increase the reliability of future flight tests. The model can be useful for UAV developers to speed up the process of designing and validating control systems