Damping Improvement of a F-16 Aircraft through Linear Matrix Inequalities

摘要

This work presents an application of Linear Matrix Inequalities (LMI) for the robust control of an F-16 aircraft through an algorithm that ensuring the damping factor to the closed-loop system. The results of some tests show that the zero and gain settings are sufficient to ensure robust performance and stability with respect to various operation points. This is one of the main characteristics of LMIs, which are mathematical tools widely applied in control theory, which allow the simultaneous treatment of several performance and robustness requirements. The pole placement is the technique used with the aim to put the system poles in closed-loop in a specific region of the complex plane. Test results using a lateral dynamic model of the F-16 aircraft are presented and discussed.