Backstepping design of missile guidance and control based on adaptive fuzzy sliding mode control

被引：53
|
作者：
Ran Maopeng [1 ]
Wang Qing [1 ]
Hou Delong [1 ]
Dong Chaoyang [2 ]
机构：
[1] Beihang Univ, Sch Automat Sci & Elect Engn, Beijing 100191, Peoples R China
[2] Beihang Univ, Sch Aeronaut Sci & Engn, Beijing 100191, Peoples R China
来源：
CHINESE JOURNAL OF AERONAUTICS | 2014年 / 27卷 / 03期
基金：
中国国家自然科学基金;
关键词：
Adaptive fuzzy system; Backstepping; Integrated guidance and control; Nonlinear; Sliding mode control; INTEGRATED GUIDANCE; AUTOPILOT;
D O I：
10.1016/j.cja.2014.04.007
中图分类号：
V [航空、航天];
学科分类号：
08 ; 0825 ;
摘要：
This paper presents an integrated missile guidance and control law based on adaptive fuzzy sliding mode control. The integrated model is formulated as a block-strict-feedback nonlinear system, in which modeling errors, unmodeled nonlinearities, target maneuvers, etc. are viewed as unknown uncertainties. The adaptive nonlinear control law is designed based on backstepping and sliding mode control techniques. An adaptive fuzzy system is adopted to approximate the coupling nonlinear functions of the system, and for the uncertainties, we utilize an online-adaptive control law to estimate the unknown parameters. The stability analysis of the closed-loop system is also conducted. Simulation results show that, with the application of the adaptive fuzzy sliding mode control, small miss distances and smooth missile trajectories are achieved, and the system is robust against system uncertainties and external disturbances. (C) 2014 Production and hosting by Elsevier Ltd. on behalf of CSAA & BUAA.
引用
收藏
页码：634 / 642
页数：9
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