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

Xiang Liu,Xiaogeng Liang

doi:10.1155/2019/8531584

Abstract

In this study, a novel integrated guidance and control (IGC) algorithm based on an IGC method and the asymmetric barrier Lyapunov function is designed; this algorithm is designed for the interceptor missile which uses a direct-force/aerodynamic-force control scheme. First, by considering the coupling between the pitch and the yaw channels of the interceptor missile, an IGC model of these channels is established, and a time-varying gain extended state observer (TVGESO) is designed to estimate unknown interferences in the model. Second, by considering the system output constraint problem, an asymmetric barrier Lyapunov function and a dynamic surface sliding-mode control method are employed to design the control law of the pitch and yaw channels to obtain the desired control moments. Finally, in light of redundancy in such actuators as aerodynamic rudders and jet devices, a dynamic control allocation algorithm is designed to assign the desired control moments to the actuators. Moreover, the results of simulations show that the IGC algorithm based on the asymmetric barrier Lyapunov function for the interceptor missile allows the outputs to meet the constraints and improves the stability of the control system of the interceptor missile.

Highlights

The interceptor missile plays an important role in modern anti-missile systems
Methods of Integrated guidance and control (IGC) design have been widely used in guidance and control systems of International Journal of Aerospace Engineering aircraft [10], missiles [11,12,13], and unmanned aerial vehicles [14, 15]
In view of the above analysis, to aim at the interceptor missile which uses a direct-force/aerodynamic-force control scheme, and to consider the coupling relationship between the pitch and the yaw channels as well as the constraints on the system’s output, this study proposes an IGC algorithm based on the asymmetric barrier Lyapunov function

Summary

Introduction

The interceptor missile plays an important role in modern anti-missile systems. Given the rapid development of hypersonic aircraft, demands on accurate guidance and control of the interceptor missile has become increasingly stringent. By combining barrier Lyapunov functions with dynamic surface control technologies, some studies [30, 31] have proposed barrier Lyapunov function-based methods suitable for constrained dynamic surface control to solve the computational inflation problem caused by backstepping control Researchers subsequently applied this method to brushless DC motors [32], plane braking systems [33], and hypersonic aircraft [34, 35] to achieve satisfactory results in terms of constrained control. Design methods based on barrier Lyapunov functions are advantageous because they can solve the output constraint problem of interceptor missile guidance control systems and improve their stability. In view of the above analysis, to aim at the interceptor missile which uses a direct-force/aerodynamic-force control scheme, and to consider the coupling relationship between the pitch and the yaw channels as well as the constraints on the system’s output, this study proposes an IGC algorithm based on the asymmetric barrier Lyapunov function. The results of simulations show that the proposed algorithm enables the outputs to meet the constraints and improves the stability of the interceptor missile control systems

IGC Model of Interceptor Missile

Design of TVGESO

Dynamic Control Allocation Algorithm

Simulation Analysis

Conclusion