Integrated Missile Guidance and Control Design with Smooth Adaptive Sliding Mode Control

被引：0

作者：

Zhou Jialing ^{[1
,2
]}

Yang Jianying ^{[1
,2
]}

机构：

[1] Peking Univ, Coll Engn, Dept Mech & Engn Sci, State Key Lab Turbulence & Complex Syst, Beijing 100871, Peoples R China

[2] Natl Key Lab Sci & Technol Aerosp Intelligence Co, Beijing 100854, Peoples R China

来源：

2015 34TH CHINESE CONTROL CONFERENCE (CCC) | 2015年

关键词：

Missile Interception; Integrated Guidance and Control; Anti-chattering; Adaptive Sliding Mode 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 considers the problem of a missile intercepting a maneuvering target with demand for fast finite-time convergence and anti-chattering. Based on the widely used proportional navigation strategy, a novel integrated guidance and control (IGC) scheme is proposed, which is formulated as a second-order affine nonlinear system with uncertainties. Then the smooth adaptive nonsingular terminal sliding mode control (SANTSMC) method which is proposed in our pervious work is applied to this IGC scheme. By virtue of the SANTSMC method, the uncertainties with unknown bounds can be addressed, fast finite-time convergence can be achieved, and the chattering problem can be well solved.

引用

页码：5206 / 5211

页数：6

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