Design and Simulation of Aircraft Pitch Control Using Matrix Transformation Techniques

Abstract

Aircraft pitch control is very important in take-off and stabilization. This critical criterion exists because the pitch can cause the aircraft to be in turbulence if the aircraft's pitch control is not calibrated correctly. However, controlling this parameter is not an easy task and challenging to be solved. This research aims to design a controller used on aircraft pitches control using the matrix transformation technique. The proposed technique makes it possible to obtain linear state feedback control in an explicit form with the desired eigenvalue. Furthermore, the proposed technique can improve response time, stability, and handling various flight conditions compared to conventional PID. The proposed technique uses transformation matrix T to find the feedback gain matrix K . The controller is used to find out the response value by several experiments with fixed setpoints, changed setpoints, and by adding load to the system. Based on the results with a fixed setpoint, the system response has 0.47 s time constant, and 0.39 s delay time. The simulations show the system response can follow the setpoint well without any overshoot.