Robust Control of a Dynamic Model of an F-16 Aircraft with Improved Damping through Linear Matrix Inequalities

This work presents an application of Linear Matrix
Inequalities (LMI) for the robust control of an F-16 aircraft through
an algorithm ensuring the damping factor to the closed loop system.
The results show that the zero and gain settings are sufficient to ensure
robust performance and stability with respect to various operating
points. The technique used is the pole placement, which aims to put
the system in closed loop poles in a specific region of the complex
plane. Test results using a dynamic model of the F-16 aircraft are
presented and discussed.

Authors:

• J. P. P. Andrade
• V. A. F. Campos

Keywords:

• F-16 Aircraft
• linear matrix inequalities
• pole placement
• robust control.

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