Abstract
An aircraft is unstable in longitudinal motion, the variation of aerodynamic derivatives and center-of-gravity position caused by altitude, speed, and fuel have a great impact on the control and stability of the aircraft. By using the Linear Matrix Inequality (LMI) approach, the longitudinal static stability of the aircraft is compensated. In addition, the pitch attitude control system is designed, and multi-objective control, including pole assignment and controlled variable constraints, is achieved during the designing process. As a result, the robustness of the system is also achieved. Finally, the simulation results of the pitch attitude control system show that this design approach is feasible.
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