Adaptive sliding mode attitude controller design for multi-missile cooperation

Guangyuan Shao; Hao Fang; Xueyuan Wang

doi:10.1109/ICMA.2015.7237605

Adaptive sliding mode attitude controller design for multi-missile cooperation

Guangyuan Shao
, Hao Fang
, Xueyuan Wang

School of Automation

Beijing Institute of Technology

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

2 Citations (Scopus)

Abstract

To deal with the problem of missile attitude control in the case of multi-missile formation, a quaternion missile model, which is a second order nonlinear system, is proposed in this note. Based on the quaternion model, a two-layer sliding mode controller is designed to track the desired attitude angles for a missile to achieve the 3-missile formation flight. The special two-layer structure of the controller makes it possible to meet the requirements of the attitude control for multi-missile cooperation. To solve the problems of the uncertainties in the system, an adaptive item is added to the controller. Also, the stability of the closed-loop system is analyzed. The simulation results illustrate that attitudes of the missile can converge to the references well.

Original language	English
Title of host publication	2015 IEEE International Conference on Mechatronics and Automation, ICMA 2015
Publisher	Institute of Electrical and Electronics Engineers Inc.
Pages	899-904
Number of pages	6
ISBN (Electronic)	9781479970964
DOIs	https://doi.org/10.1109/ICMA.2015.7237605
Publication status	Published - 2 Sept 2015
Event	12th IEEE International Conference on Mechatronics and Automation, ICMA 2015 - Beijing, China Duration: 2 Aug 2015 → 5 Aug 2015

Publication series

Name	2015 IEEE International Conference on Mechatronics and Automation, ICMA 2015

Conference

Conference	12th IEEE International Conference on Mechatronics and Automation, ICMA 2015
Country/Territory	China
City	Beijing
Period	2/08/15 → 5/08/15

Keywords

Multi-missile cooperation
missile attitude angles
quaternion model
sliding mode control

Access to Document

10.1109/ICMA.2015.7237605

Cite this

Shao, G., Fang, H., & Wang, X. (2015). Adaptive sliding mode attitude controller design for multi-missile cooperation. In 2015 IEEE International Conference on Mechatronics and Automation, ICMA 2015 (pp. 899-904). Article 7237605 (2015 IEEE International Conference on Mechatronics and Automation, ICMA 2015). Institute of Electrical and Electronics Engineers Inc.. https://doi.org/10.1109/ICMA.2015.7237605

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title = "Adaptive sliding mode attitude controller design for multi-missile cooperation",

abstract = "To deal with the problem of missile attitude control in the case of multi-missile formation, a quaternion missile model, which is a second order nonlinear system, is proposed in this note. Based on the quaternion model, a two-layer sliding mode controller is designed to track the desired attitude angles for a missile to achieve the 3-missile formation flight. The special two-layer structure of the controller makes it possible to meet the requirements of the attitude control for multi-missile cooperation. To solve the problems of the uncertainties in the system, an adaptive item is added to the controller. Also, the stability of the closed-loop system is analyzed. The simulation results illustrate that attitudes of the missile can converge to the references well.",

keywords = "Multi-missile cooperation, missile attitude angles, quaternion model, sliding mode control",

author = "Guangyuan Shao and Hao Fang and Xueyuan Wang",

note = "Publisher Copyright: {\textcopyright} 2015 IEEE.; 12th IEEE International Conference on Mechatronics and Automation, ICMA 2015 ; Conference date: 02-08-2015 Through 05-08-2015",

year = "2015",

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doi = "10.1109/ICMA.2015.7237605",

language = "English",

series = "2015 IEEE International Conference on Mechatronics and Automation, ICMA 2015",

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Shao, G, Fang, H & Wang, X 2015, Adaptive sliding mode attitude controller design for multi-missile cooperation. in 2015 IEEE International Conference on Mechatronics and Automation, ICMA 2015., 7237605, 2015 IEEE International Conference on Mechatronics and Automation, ICMA 2015, Institute of Electrical and Electronics Engineers Inc., pp. 899-904, 12th IEEE International Conference on Mechatronics and Automation, ICMA 2015, Beijing, China, 2/08/15. https://doi.org/10.1109/ICMA.2015.7237605

Adaptive sliding mode attitude controller design for multi-missile cooperation. / Shao, Guangyuan; Fang, Hao; Wang, Xueyuan.
2015 IEEE International Conference on Mechatronics and Automation, ICMA 2015. Institute of Electrical and Electronics Engineers Inc., 2015. p. 899-904 7237605 (2015 IEEE International Conference on Mechatronics and Automation, ICMA 2015).

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

TY - GEN

T1 - Adaptive sliding mode attitude controller design for multi-missile cooperation

AU - Shao, Guangyuan

AU - Fang, Hao

AU - Wang, Xueyuan

PY - 2015/9/2

Y1 - 2015/9/2

N2 - To deal with the problem of missile attitude control in the case of multi-missile formation, a quaternion missile model, which is a second order nonlinear system, is proposed in this note. Based on the quaternion model, a two-layer sliding mode controller is designed to track the desired attitude angles for a missile to achieve the 3-missile formation flight. The special two-layer structure of the controller makes it possible to meet the requirements of the attitude control for multi-missile cooperation. To solve the problems of the uncertainties in the system, an adaptive item is added to the controller. Also, the stability of the closed-loop system is analyzed. The simulation results illustrate that attitudes of the missile can converge to the references well.

AB - To deal with the problem of missile attitude control in the case of multi-missile formation, a quaternion missile model, which is a second order nonlinear system, is proposed in this note. Based on the quaternion model, a two-layer sliding mode controller is designed to track the desired attitude angles for a missile to achieve the 3-missile formation flight. The special two-layer structure of the controller makes it possible to meet the requirements of the attitude control for multi-missile cooperation. To solve the problems of the uncertainties in the system, an adaptive item is added to the controller. Also, the stability of the closed-loop system is analyzed. The simulation results illustrate that attitudes of the missile can converge to the references well.

KW - Multi-missile cooperation

KW - missile attitude angles

KW - quaternion model

KW - sliding mode control

UR - https://www.scopus.com/pages/publications/84955237441

U2 - 10.1109/ICMA.2015.7237605

DO - 10.1109/ICMA.2015.7237605

M3 - Conference contribution

AN - SCOPUS:84955237441

T3 - 2015 IEEE International Conference on Mechatronics and Automation, ICMA 2015

SP - 899

EP - 904

BT - 2015 IEEE International Conference on Mechatronics and Automation, ICMA 2015

PB - Institute of Electrical and Electronics Engineers Inc.

T2 - 12th IEEE International Conference on Mechatronics and Automation, ICMA 2015

Y2 - 2 August 2015 through 5 August 2015

ER -

Shao G, Fang H, Wang X. Adaptive sliding mode attitude controller design for multi-missile cooperation. In 2015 IEEE International Conference on Mechatronics and Automation, ICMA 2015. Institute of Electrical and Electronics Engineers Inc. 2015. p. 899-904. 7237605. (2015 IEEE International Conference on Mechatronics and Automation, ICMA 2015). doi: 10.1109/ICMA.2015.7237605

Adaptive sliding mode attitude controller design for multi-missile cooperation

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