Nonlinear integrated guidance and control based on adaptive backstepping scheme

Abstract

Purpose The purpose of this paper is to design an adaptive nonlinear controller for a nonlinear system of integrated guidance and control. Design/methodology/approach A nonlinear integrated guidance and control approach is applied to a homing, tail-controlled air vehicle. Adaptive backstepping controller technique is used to deal with the problem, and the Lyapanov theory is used in the stability analysis of the nonlinear system. A nonlinear model of normal force coefficient is obtained from an existing nonlinear model of lift coefficient which was validated by open loop response. The simulation was performed in the pitch plane to prove the benefits of the proposed scheme; however, it can be readily extended to all the three axes. Findings Monte Carlo simulations indicate that using nonlinear adaptive backstepping formulation meaningfully improves the performance of the system, while it ensures stability of a nonlinear system. Practical implications The proposed method could be used to obtain better performance of hit to kill accuracy without the expense of control effort. Originality/value A nonlinear adaptive backstepping controller for nonlinear aerodynamic air vehicle is designed and guaranteed to be stable which is a novel-based approach to the integrated guidance and control. This method makes noticeable performance improvement, and it can be used with hit to kill accuracy.

Integrated Guidance and Control of Interceptor Missile Based on Asymmetric Barrier Lyapunov Function

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“…By substituting v z42 with the estimated values of TVGESO in Equation (12), one can design the dynamic sliding-mode control law of the interceptor missile as shown in Equation 30:…”

Integrated Guidance and Control Design of Rolling‐Guided Projectile Based on Adaptive Fuzzy Control with Multiple Constraints

“…Based on the relative motion between the projectile and target, the control law of canard deflection can be directly calculated by IGC algorithm. Scholars have subsequently achieved results in IGC, combining it with robust control [7,8], dynamic surface control [9,10], adaptive control [7][8][9], sliding mode control (SMC) [11][12][13][14], fuzzy control [15], and other modern control theories. Yang et al [7] proposed a robust IGC design method for guided projectile based on a SMC observer.…”

“…erefore, Seyedipour et al [9] designed a dynamic surface and adopted a low-pass filter to avoid differential expansion, which simplified the design process by guaranteeing the guidance performance and system stability. Combining it with ESO, Shao and Wang [10] designed a dynamic surface backstepping controller.…”

Research on Integrated Guidance and Control of Distributed Cooperation of Multi-Interceptor with State Coupling

“…The sliding-mode control method has been widely used in the design of IGC of aircraft [17], missile [18], and unmanned helicopter [19,20]. In existing papers, most of them were designed in a single channel [21,22], regardless of the coupling between channels. The authors in [23,24] designed IGC algorithms in three dimensions, but designing the controller is difficult when establishing the model with a high order.…”