Unstable Aircraft Flight Control Based on Linear Matrix Inequality with Consideration of Control and Saturation Constraints

Document Type : Research Article

Authors

Shahid Beheshti University

Abstract

In this paper, limitation in actuator capacity has been used as a key role in the design of the flight control system. In order to guarantee the performance and stability of flight control systems in the presence of saturation, in flying high angle of attack area, the development of linear matrix inequality, optimization techniques, and numerical methods are proposed. Also, in this paper, the combination of two anti-windup methods and the direct saturation method in the tracking problem of the flight path angle is discussed. For this purpose, the nonlinear model of the aircraft is modeled, moreover the linear model is obtained at the trim operation conditions. Then the controller is designed to track flight path angle maneuver regardless of saturation. In the following, considering the maximum disturbance involved in aircraft maneuvering, a safe controller that guarantees performance and stability is designed, and the gain scheduling technique to prevent conservatism in the use of controllers is applied. The results of the nonlinear and linear model of the aircraft are presented in tracking flight path angle atahigh angle of attack with consideration of control and saturation constraints in unstable operation conditions. Simulation results indicate the improvement of the mentioned control method for an unstable aircraft. 

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References

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Amirkabir Journal of Mechanical Engineering
Volume 53, Issue 2
May 2021
Pages 979-992

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