Adaptive Integrated Guidance and Fault Tolerant Control Using Backstepping and Sliding Mode

被引：8
|
作者：
Jegarkandi, Mohsen Fathi [1 ]
Ashrafifar, Asghar [1 ]
Mohsenipour, Reza [1 ]
机构：
[1] Sharif Univ Technol, Dept Aerosp Engn, Tehran, Iran
来源：
INTERNATIONAL JOURNAL OF AEROSPACE ENGINEERING | 2015年 / 2015卷
关键词：
MISSILE GUIDANCE; DESIGN; LAW;
D O I：
10.1155/2015/253478
中图分类号：
V [航空、航天];
学科分类号：
08 ; 0825 ;
摘要：
A new method of integrated guidance and control for homing missiles with actuator fault against manoeuvring targets is proposed. Model of the integrated guidance and control system in the pitch plane with actuator fault and some uncertainty is developed. A control law using combination of adaptive backstepping and sliding mode approaches is designed to achieve interception in the presence of bounded uncertainties and actuator fault. Simulation results show that new approach has better performance than adaptive backstepping and has good performance in the presence of actuator fault.
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收藏
页数：7
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