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

页码：238 / +

页数：2

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