Missile Autopilot Design Using Backstepping Approach

被引：2
|
作者：
Lin De-fu [1 ]
Fan Jun-fang [2 ]
机构：
[1] Beijing Inst Technol, Dept Flying Vehicle Design, Beijing 100081, Peoples R China
[2] BeijingSinskTek Co Ltd, Beijing 100040, Peoples R China
来源：
SECOND INTERNATIONAL CONFERENCE ON COMPUTER AND ELECTRICAL ENGINEERING, VOL 1, PROCEEDINGS | 2009年
关键词：
missile control; acceleration autopilot; backstepping; optimal control;
D O I：
10.1109/ICCEE.2009.51
中图分类号：
TP18 [人工智能理论];
学科分类号：
081104 ; 0812 ; 0835 ; 1405 ;
摘要：
The autopilot design process is detailed from a backstepping control perspective. The control parameters were determined based on step and sine input commands. Then both characteristics and effect of two control parameters were examined. A linear three-loop topology was also presented for comparison. The results show that the backstepping recursive approach provides a systematically constructive procedure for acceleration autopilot. The based nonlinear autopilot exhibits excellent tracking and robustness.
引用
收藏
页码：238 / +
页数：2
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