Analysis of Yaw-axis Control Performance According to Motor Canted Angle of eVTOL Aircraft

In this thesis, the yaw-axis control performance according to the motor/prop canted angle was analyzed through simulation to ensure the flight performance of an eVTOL aircraft, which are recently being developed around the world. The method for yaw axis control was investigated using various shapes and configurations of urban air mobility aircraft. ADS-33E, which is the standard for evaluating the flight characteristics of rotary wing aircraft, was examined. In addition, yaw-torque characteristics due to thrust changes depending on the canted angle were probed and simulated using a linear dynamics model to construct a PID controller. The optimal initial control gain was selected based on frequency, and then the final control gain was determined by considering motor saturation. The results from the yaw-axis control simulation for each canted angle confirmed that the canted angle was essential for eVTOL aircraft, which have a larger Z-axis moment of inertia than multicopters. © ICROS 2024.