Adaptive control for missile systems with parameter uncertainty

Zhiwei Lin; Zheng Zhu; Yuanqing Xia; Shuo Wang

Adaptive control for missile systems with parameter uncertainty

Zhiwei Lin^*
, Zheng Zhu
, Yuanqing Xia
, Shuo Wang

^*此作品的通讯作者

自动化学院

Beijing Institute of Technology
CAS - Institute of Automation

科研成果: 期刊稿件 › 文章 › 同行评审

5 引用（Scopus）

摘要

This paper is devoted to attitude control of a nonlinear missile model. Combining the back-stepping technique, the corresponding sliding mode controller is designed to guarantee the state variables of the closed loop system to converge to the reference state with the help of the adaptive law by estimating the total uncertainties. Also, simulation results are presented to illustrate the effectiveness of the control strategy.

源语言	英语
页（从-至）	1937-1944
页数	8
期刊	ICIC Express Letters
卷	4
期	5 B
出版状态	已出版 - 10月 2010

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title = "Adaptive control for missile systems with parameter uncertainty",

abstract = "This paper is devoted to attitude control of a nonlinear missile model. Combining the back-stepping technique, the corresponding sliding mode controller is designed to guarantee the state variables of the closed loop system to converge to the reference state with the help of the adaptive law by estimating the total uncertainties. Also, simulation results are presented to illustrate the effectiveness of the control strategy.",

keywords = "Adaptive control, Back-stepping, Missile attitude Control, Sliding mode control",

author = "Zhiwei Lin and Zheng Zhu and Yuanqing Xia and Shuo Wang",

year = "2010",

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language = "English",

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T1 - Adaptive control for missile systems with parameter uncertainty

AU - Lin, Zhiwei

AU - Zhu, Zheng

AU - Xia, Yuanqing

AU - Wang, Shuo

PY - 2010/10

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N2 - This paper is devoted to attitude control of a nonlinear missile model. Combining the back-stepping technique, the corresponding sliding mode controller is designed to guarantee the state variables of the closed loop system to converge to the reference state with the help of the adaptive law by estimating the total uncertainties. Also, simulation results are presented to illustrate the effectiveness of the control strategy.

AB - This paper is devoted to attitude control of a nonlinear missile model. Combining the back-stepping technique, the corresponding sliding mode controller is designed to guarantee the state variables of the closed loop system to converge to the reference state with the help of the adaptive law by estimating the total uncertainties. Also, simulation results are presented to illustrate the effectiveness of the control strategy.

KW - Adaptive control

KW - Back-stepping

KW - Missile attitude Control

KW - Sliding mode control

UR - https://www.scopus.com/pages/publications/77956930206

M3 - Article

AN - SCOPUS:77956930206

SN - 1881-803X

VL - 4

SP - 1937

EP - 1944

JO - ICIC Express Letters

JF - ICIC Express Letters

IS - 5 B

ER -

Adaptive control for missile systems with parameter uncertainty

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