Yüksek atalet ve tasarım sınırlarını aşar yük etkisi altındaki kontrol yüzeylerinin modellenmesi ve kontrolü

The study aims to model the entire flight control actuation system of an airplane, extending from the flight control computer to the control surfaces, and determine the appropriate control parameters considering factors such as inertia and abusive load. Mathematical model of the hydraulic cylinder, flow characteristics of the direct-drive valve, and the linear force motor behaviour that operates the direct drive valve are implemented in the MATLAB Simulink software environment. Control parameters of the system, which are composed of two nested control loops, are determined by simulating the system starting from the inner loop. At this stage, a PID controller was utilized, and the control parameters were determined by considering the root locus analysis. The model was validated with the experimental setup established in the test environment. The study focuses on determining the controller parameters to maintain the system's performance within the required actuator bandwidth and speed, despite the inertial effects.