An observer-based missile guidance law

Zheng Zhu; Yuanqing Xia; Mengyin Fu; Shuo Wang

doi:10.1109/CCDC.2011.5968387

An observer-based missile guidance law

Zheng Zhu^*, Yuanqing Xia, Mengyin Fu, Shuo Wang

^*Corresponding author for this work

School of Automation

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution › peer-review

2 Citations (Scopus)

Abstract

Nonlinear sliding mode guidance laws with finite time convergence are derived for the missile interception in this paper. The proposed guidance laws guarantee that the missile can intercept a maneuverable target with unknown target acceleration. Specially, the control design consists of the estimation of the target acceleration by extended state observer (ESO) and thus it achieves the decrease of undesired chattering effectively. Also, simulation results are presented to illustrate the effectiveness of the control strategies.

Original language	English
Title of host publication	Proceedings of the 2011 Chinese Control and Decision Conference, CCDC 2011
Pages	1282-1287
Number of pages	6
DOIs	https://doi.org/10.1109/CCDC.2011.5968387
Publication status	Published - 2011
Event	2011 Chinese Control and Decision Conference, CCDC 2011 - Mianyang, China Duration: 23 May 2011 → 25 May 2011

Publication series

Name	Proceedings of the 2011 Chinese Control and Decision Conference, CCDC 2011

Conference

Conference	2011 Chinese Control and Decision Conference, CCDC 2011
Country/Territory	China
City	Mianyang
Period	23/05/11 → 25/05/11

Keywords

ESO
Finite-time control
Guidance law
Sliding mode control

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10.1109/CCDC.2011.5968387

Cite this

@inproceedings{062a3776089e49308d11ed478421dfac,

title = "An observer-based missile guidance law",

abstract = "Nonlinear sliding mode guidance laws with finite time convergence are derived for the missile interception in this paper. The proposed guidance laws guarantee that the missile can intercept a maneuverable target with unknown target acceleration. Specially, the control design consists of the estimation of the target acceleration by extended state observer (ESO) and thus it achieves the decrease of undesired chattering effectively. Also, simulation results are presented to illustrate the effectiveness of the control strategies.",

keywords = "ESO, Finite-time control, Guidance law, Sliding mode control",

author = "Zheng Zhu and Yuanqing Xia and Mengyin Fu and Shuo Wang",

year = "2011",

doi = "10.1109/CCDC.2011.5968387",

language = "English",

isbn = "9781424487363",

series = "Proceedings of the 2011 Chinese Control and Decision Conference, CCDC 2011",

pages = "1282--1287",

booktitle = "Proceedings of the 2011 Chinese Control and Decision Conference, CCDC 2011",

note = "2011 Chinese Control and Decision Conference, CCDC 2011 ; Conference date: 23-05-2011 Through 25-05-2011",

}

Zhu, Z, Xia, Y, Fu, M & Wang, S 2011, An observer-based missile guidance law. in Proceedings of the 2011 Chinese Control and Decision Conference, CCDC 2011., 5968387, Proceedings of the 2011 Chinese Control and Decision Conference, CCDC 2011, pp. 1282-1287, 2011 Chinese Control and Decision Conference, CCDC 2011, Mianyang, China, 23/05/11. https://doi.org/10.1109/CCDC.2011.5968387

An observer-based missile guidance law. / Zhu, Zheng; Xia, Yuanqing; Fu, Mengyin et al.
Proceedings of the 2011 Chinese Control and Decision Conference, CCDC 2011. 2011. p. 1282-1287 5968387 (Proceedings of the 2011 Chinese Control and Decision Conference, CCDC 2011).

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution › peer-review

TY - GEN

T1 - An observer-based missile guidance law

AU - Zhu, Zheng

AU - Xia, Yuanqing

AU - Fu, Mengyin

AU - Wang, Shuo

PY - 2011

Y1 - 2011

N2 - Nonlinear sliding mode guidance laws with finite time convergence are derived for the missile interception in this paper. The proposed guidance laws guarantee that the missile can intercept a maneuverable target with unknown target acceleration. Specially, the control design consists of the estimation of the target acceleration by extended state observer (ESO) and thus it achieves the decrease of undesired chattering effectively. Also, simulation results are presented to illustrate the effectiveness of the control strategies.

AB - Nonlinear sliding mode guidance laws with finite time convergence are derived for the missile interception in this paper. The proposed guidance laws guarantee that the missile can intercept a maneuverable target with unknown target acceleration. Specially, the control design consists of the estimation of the target acceleration by extended state observer (ESO) and thus it achieves the decrease of undesired chattering effectively. Also, simulation results are presented to illustrate the effectiveness of the control strategies.

KW - ESO

KW - Finite-time control

KW - Guidance law

KW - Sliding mode control

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U2 - 10.1109/CCDC.2011.5968387

DO - 10.1109/CCDC.2011.5968387

M3 - Conference contribution

AN - SCOPUS:80052223354

SN - 9781424487363

T3 - Proceedings of the 2011 Chinese Control and Decision Conference, CCDC 2011

SP - 1282

EP - 1287

BT - Proceedings of the 2011 Chinese Control and Decision Conference, CCDC 2011

T2 - 2011 Chinese Control and Decision Conference, CCDC 2011

Y2 - 23 May 2011 through 25 May 2011

ER -

An observer-based missile guidance law

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