Backstepping Sliding Mode Control for Missile Attitude System

被引：0

作者：

Huang Zi-rui ^{[1
]}

Wu Yun-jie ^{[1
]}

Zuo Jing-xing ^{[1
]}

Cheng Ling ^{[2
]}

机构：

[1] Beihang Univ, Sch Automat Sci & Elect Engn, Beijing 100083, Peoples R China

[2] Beijing New Aerotropolis, Beijing 102602, Peoples R China

来源：

2018 IEEE CSAA GUIDANCE, NAVIGATION AND CONTROL CONFERENCE (CGNCC) | 2018年

关键词：

missile attitude control; sliding mode control; backstepping; NONLINEAR-SYSTEMS; ADAPTIVE-CONTROL;

D O I：

暂无

中图分类号：

TP [自动化技术、计算机技术];

学科分类号：

0812 ;

摘要：

This paper is devoted to the attitude control of a quaternion described missile model, which is nonlinear in aerodynamics with atmospheric moment uncertainties, inertia uncertainties, bounded disturbances and actuator failures. One backstepping sliding mode controller is designed to guarantee the state variables of the closed -loop system to converge to a small region of the reference states. The variable structure control including sliding mode control has the valuable features of anti-interference and resisting parameter distortion, providing a useful solution for designing control law. Also, simulation results are presented to illustrate the effectiveness of the control strategy.

引用

页数：6

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