Optimal Feedback Linearization Control of Wing Rock by Using NSGA_II

Wing rock is one of the well known instabilities that occurs in aircraft dynamics at moderate to high angles of attack. In this phenomenon aircraft dynamics can display an oscillatory lateral behavior that manifests itself as a limit cycle known as wing rock. The main objective of this work is to tune the feedback linearization controller in an optimal way, for obtaining an accurate wing rock controller. NSGA_II method was used to tune the designed controller in aim to decrease the controller tracking error. The simulation result showed that the proposed method tuned the controller efficiently.

Keywords:

wing rock , nonlinear model , feedback linearization , optimal control , NSGA_II