Abstract
This paper presents a hybrid robust control design method for a third-order lower-triangular model of nonlinear dynamic systems in the presence of disturbance. In this paper, a novel control design is presented systematically to synthesize a robust nonlinear feedback controller, called backstepping sliding mode control (BSMC), for the proposed system by a combined approach of backstepping design and sliding mode control. In this approach, a family of the “sliding surface” is introduced in state transformations. Then, a smooth switching function of the sliding surface is introduced and enforced to include in virtual feedbacks and a real control law from the control selection phrases of the backstepping design loop. The achieved control method proves a well-tracking command with asymptotic stability, provides a robustness in the presence of uncertainties, and eliminates completely a chattering phenomenon. The application of flight-path angle control corresponding to the longitudinal dynamics of a high-performance F-16 aircraft simulation model is implemented. Under some assumptions, full nonlinear longitudinal dynamics is reformed into a lower-triangular system for a direct application to formulate a control law. A closed-loop system is achieved for in-flight simulation with different flight profiles for a comparison of the existing methods. Also, an external disturbance on different loading/unloading conditions in flight is applied to verify and validate robustness of the proposed control method.
Highlights
A standard design method of the flight control system for nonlinear aircraft dynamic systems is based on gain scheduling from linear control system designs
A hybrid robust control design method is proposed for a third-order SingleInput Single-Output (SISO) lower-triangular model of nonlinear dynamic systems in the presence of disturbances. en, the application of flight-path angle control corresponding to the longitudinal dynamics of γ
A high-performance F-16 aircraft simulation model is implemented. e contributions of this paper are as follows: (i) e proposed control method provides a diversity of nonlinear control design tools to a specific class of nonlinear dynamic systems and has a high potential for other application in engineering systems
Summary
A standard design method of the flight control system for nonlinear aircraft dynamic systems is based on gain scheduling from linear control system designs. A better approach in robust control methods [6, 7] is proposed to improve the handling qualities across the specified flight envelope without the use of gain scheduling In this approach, the control parameters of dynamic inversion are designed to minimize the probability of violating design specifications and so provide a better design with good robustness in stability and performance subject to modeling uncertainties. A new control design method is presented for formulating a backstepping sliding mode control (BSMC) law for the (SISO) third-order lower-triangular form of the nonlinear dynamic system. A global asymptotic stability is achieved with no or acceptably small overshoot in the presence of the model parameter errors and external disturbances
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