Design and Simulation of Aircraft Pitch Control Using Matrix Transformation Techniques
Hikmat Oka Kusuma *
Department of Electrical Engineering, Faculty of Engineering, University Negeri Surabaya, Surabaya, Indonesia.
Unit Three Kartini
Department of Electrical Engineering, Faculty of Engineering, University Negeri Surabaya, Surabaya, Indonesia.
Bambang Suprianto
Department of Electrical Engineering, Faculty of Engineering, University Negeri Surabaya, Surabaya, Indonesia.
Rifqi Firmansyah *
Department of Electrical Engineering, Faculty of Engineering, University Negeri Surabaya, Surabaya, Indonesia.
Fandik A. K
Department of Electrical Engineering, Faculty of Engineering, University Negeri Surabaya, Surabaya, Indonesia.
Nugroho S. D.
Department of Electrical Engineering, Faculty of Engineering, University Negeri Surabaya, Surabaya, Indonesia.
Aldo T. P.
Department of Electrical Engineering, Faculty of Engineering, University Negeri Surabaya, Surabaya, Indonesia.
Nabila Hanunnisa
Department of Electrical Engineering, Faculty of Engineering, University Negeri Surabaya, Surabaya, Indonesia.
*Author to whom correspondence should be addressed.
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.
Keywords: Aircraft pitch, overshooting control, ackerman formula, transformation matrix t