Design and validation of rotor mode control for a tilt-wing aircraft

Abstract To address the flight control issue of tiltrotor airfoils in rotor mode, a series proportional-integral-derivative (PID) control approach is employed to simulate and validate its flight performance during hovering and vertical takeoff and landing phases. The designed series PID controller exhibits a swift reaction rate in hover, step response, and sinusoidal response evaluations. It sustains little steady-state error and attains elevated tracking precision. These properties allow it to efficiently satisfy the dynamic stabilization demands for vertical takeoff and landing, in addition to attitude control. The system has exceptional dynamic control precision and responsiveness in rotor mode.