Fast limit protection design: A terminal sliding mode control method

Yiwen Qi; Wen Bao; Juntao Chang; Jianguo Cui

doi:10.1109/ChiCC.2014.6896590

Fast limit protection design: A terminal sliding mode control method

Yiwen Qi^*
, Wen Bao
, Juntao Chang
, Jianguo Cui

^*Corresponding author for this work

Shenyang Aerospace University
School of Energy Science and Engineering, Harbin Institute of Technology

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

1 Scopus citations

Abstract

In this paper, a novel limit protection control design via adaptive terminal sliding mode control technique is proposed, which addresses the inlet buzz protection problem of a ducted rocket. First, the mathematical model involving actuator (gas flow regulating system) and plant (ducted rocket engine) is briefly summarized. Then, the ducted rocket limit protection control problem is proposed and the problem solving thought is given. Next, an adaptive terminal sliding mode face is introduced to design the auxiliary limit protection sub-controller, and the control effect can provide high accuracy and fast convergence of limit protection error with a certain robustness. Moreover, on the basis of finite-time stability theory, the closed-loop system stability and finite time error convergence are proved. Finally, numerical simulation results are provided to show the effectiveness of the design.

Original language	English
Title of host publication	Proceedings of the 33rd Chinese Control Conference, CCC 2014
Editors	Shengyuan Xu, Qianchuan Zhao
Publisher	IEEE Computer Society
Pages	26-30
Number of pages	5
ISBN (Electronic)	9789881563842
DOIs	https://doi.org/10.1109/ChiCC.2014.6896590
State	Published - 11 Sep 2014
Externally published	Yes
Event	Proceedings of the 33rd Chinese Control Conference, CCC 2014 - Nanjing, China Duration: 28 Jul 2014 → 30 Jul 2014

Publication series

Name	Proceedings of the 33rd Chinese Control Conference, CCC 2014
ISSN (Print)	1934-1768
ISSN (Electronic)	2161-2927

Conference

Conference	Proceedings of the 33rd Chinese Control Conference, CCC 2014
Country/Territory	China
City	Nanjing
Period	28/07/14 → 30/07/14

Keywords

Limit protection control
ducted rocket
inlet buzz
terminal sliding mode control

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10.1109/ChiCC.2014.6896590

Cite this

@inproceedings{cf1ea22b35f641db8ea034d40ca74cd1,

title = "Fast limit protection design: A terminal sliding mode control method",

abstract = "In this paper, a novel limit protection control design via adaptive terminal sliding mode control technique is proposed, which addresses the inlet buzz protection problem of a ducted rocket. First, the mathematical model involving actuator (gas flow regulating system) and plant (ducted rocket engine) is briefly summarized. Then, the ducted rocket limit protection control problem is proposed and the problem solving thought is given. Next, an adaptive terminal sliding mode face is introduced to design the auxiliary limit protection sub-controller, and the control effect can provide high accuracy and fast convergence of limit protection error with a certain robustness. Moreover, on the basis of finite-time stability theory, the closed-loop system stability and finite time error convergence are proved. Finally, numerical simulation results are provided to show the effectiveness of the design.",

keywords = "Limit protection control, ducted rocket, inlet buzz, terminal sliding mode control",

author = "Yiwen Qi and Wen Bao and Juntao Chang and Jianguo Cui",

note = "Publisher Copyright: {\textcopyright} 2014 TCCT, CAA.; Proceedings of the 33rd Chinese Control Conference, CCC 2014 ; Conference date: 28-07-2014 Through 30-07-2014",

year = "2014",

month = sep,

day = "11",

doi = "10.1109/ChiCC.2014.6896590",

language = "英语",

series = "Proceedings of the 33rd Chinese Control Conference, CCC 2014",

publisher = "IEEE Computer Society",

pages = "26--30",

editor = "Shengyuan Xu and Qianchuan Zhao",

booktitle = "Proceedings of the 33rd Chinese Control Conference, CCC 2014",

address = "美国",

}

Qi, Y, Bao, W , Chang, J & Cui, J 2014, Fast limit protection design: A terminal sliding mode control method. in S Xu & Q Zhao (eds), Proceedings of the 33rd Chinese Control Conference, CCC 2014., 6896590, Proceedings of the 33rd Chinese Control Conference, CCC 2014, IEEE Computer Society, pp. 26-30, Proceedings of the 33rd Chinese Control Conference, CCC 2014, Nanjing, China, 28/07/14. https://doi.org/10.1109/ChiCC.2014.6896590

Fast limit protection design: A terminal sliding mode control method. / Qi, Yiwen; Bao, Wen ; Chang, Juntao et al.
Proceedings of the 33rd Chinese Control Conference, CCC 2014. ed. / Shengyuan Xu; Qianchuan Zhao. IEEE Computer Society, 2014. p. 26-30 6896590 (Proceedings of the 33rd Chinese Control Conference, CCC 2014).

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

TY - GEN

T1 - Fast limit protection design

T2 - Proceedings of the 33rd Chinese Control Conference, CCC 2014

AU - Qi, Yiwen

AU - Bao, Wen

AU - Chang, Juntao

AU - Cui, Jianguo

PY - 2014/9/11

Y1 - 2014/9/11

N2 - In this paper, a novel limit protection control design via adaptive terminal sliding mode control technique is proposed, which addresses the inlet buzz protection problem of a ducted rocket. First, the mathematical model involving actuator (gas flow regulating system) and plant (ducted rocket engine) is briefly summarized. Then, the ducted rocket limit protection control problem is proposed and the problem solving thought is given. Next, an adaptive terminal sliding mode face is introduced to design the auxiliary limit protection sub-controller, and the control effect can provide high accuracy and fast convergence of limit protection error with a certain robustness. Moreover, on the basis of finite-time stability theory, the closed-loop system stability and finite time error convergence are proved. Finally, numerical simulation results are provided to show the effectiveness of the design.

AB - In this paper, a novel limit protection control design via adaptive terminal sliding mode control technique is proposed, which addresses the inlet buzz protection problem of a ducted rocket. First, the mathematical model involving actuator (gas flow regulating system) and plant (ducted rocket engine) is briefly summarized. Then, the ducted rocket limit protection control problem is proposed and the problem solving thought is given. Next, an adaptive terminal sliding mode face is introduced to design the auxiliary limit protection sub-controller, and the control effect can provide high accuracy and fast convergence of limit protection error with a certain robustness. Moreover, on the basis of finite-time stability theory, the closed-loop system stability and finite time error convergence are proved. Finally, numerical simulation results are provided to show the effectiveness of the design.

KW - Limit protection control

KW - ducted rocket

KW - inlet buzz

KW - terminal sliding mode control

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DO - 10.1109/ChiCC.2014.6896590

M3 - 会议稿件

AN - SCOPUS:84907938934

T3 - Proceedings of the 33rd Chinese Control Conference, CCC 2014

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EP - 30

BT - Proceedings of the 33rd Chinese Control Conference, CCC 2014

A2 - Xu, Shengyuan

A2 - Zhao, Qianchuan

PB - IEEE Computer Society

Y2 - 28 July 2014 through 30 July 2014

ER -

Fast limit protection design: A terminal sliding mode control method

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