Design of aircraft center of gravity control law based on sliding mode control

Jianing Yan; Jing Zhang; Haiquan Li

doi:10.1109/AUS.2016.7748090

Design of aircraft center of gravity control law based on sliding mode control

Jianing Yan
, Jing Zhang
, Haiquan Li

School of Automation Science and Electrical Engineering

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

6 Scopus citations

Abstract

A sliding mode based active center of gravity control law is designed for the aircraft with center of gravity varying during flight. As the basis, the general scheme of the active center of gravity control system is proposed, and the mathematic model of aircraft center of gravity varying with fuel transfer is established. Then, the center of gravity control law based on sliding mode control theory is designed, which can guarantee the control error converges to zero in finite time. Finally, simulations are carried out to verify the proposed method. Simulation results show that the sliding mode based center of gravity control law can accurately and rapidly track the given command for various different fuel transfer conditions.

Original language	English
Title of host publication	AUS 2016 - 2016 IEEE/CSAA International Conference on Aircraft Utility Systems
Publisher	Institute of Electrical and Electronics Engineers Inc.
Pages	438-442
Number of pages	5
ISBN (Electronic)	9781509010875
DOIs	https://doi.org/10.1109/AUS.2016.7748090
State	Published - 17 Nov 2016
Event	2016 IEEE/CSAA International Conference on Aircraft Utility Systems, AUS 2016 - Beijing, China Duration: 10 Oct 2016 → 12 Oct 2016

Publication series

Name	AUS 2016 - 2016 IEEE/CSAA International Conference on Aircraft Utility Systems

Conference

Conference	2016 IEEE/CSAA International Conference on Aircraft Utility Systems, AUS 2016
Country/Territory	China
City	Beijing
Period	10/10/16 → 12/10/16

Access to Document

10.1109/AUS.2016.7748090

Cite this

Yan, J., Zhang, J., & Li, H. (2016). Design of aircraft center of gravity control law based on sliding mode control. In AUS 2016 - 2016 IEEE/CSAA International Conference on Aircraft Utility Systems (pp. 438-442). Article 7748090 (AUS 2016 - 2016 IEEE/CSAA International Conference on Aircraft Utility Systems). Institute of Electrical and Electronics Engineers Inc.. https://doi.org/10.1109/AUS.2016.7748090

@inproceedings{bc696a0cdc364911a68a5607c2e7126f,

title = "Design of aircraft center of gravity control law based on sliding mode control",

abstract = "A sliding mode based active center of gravity control law is designed for the aircraft with center of gravity varying during flight. As the basis, the general scheme of the active center of gravity control system is proposed, and the mathematic model of aircraft center of gravity varying with fuel transfer is established. Then, the center of gravity control law based on sliding mode control theory is designed, which can guarantee the control error converges to zero in finite time. Finally, simulations are carried out to verify the proposed method. Simulation results show that the sliding mode based center of gravity control law can accurately and rapidly track the given command for various different fuel transfer conditions.",

author = "Jianing Yan and Jing Zhang and Haiquan Li",

note = "Publisher Copyright: {\textcopyright} 2016 IEEE.; 2016 IEEE/CSAA International Conference on Aircraft Utility Systems, AUS 2016 ; Conference date: 10-10-2016 Through 12-10-2016",

year = "2016",

month = nov,

day = "17",

doi = "10.1109/AUS.2016.7748090",

language = "英语",

series = "AUS 2016 - 2016 IEEE/CSAA International Conference on Aircraft Utility Systems",

publisher = "Institute of Electrical and Electronics Engineers Inc.",

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booktitle = "AUS 2016 - 2016 IEEE/CSAA International Conference on Aircraft Utility Systems",

address = "美国",

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Yan, J, Zhang, J & Li, H 2016, Design of aircraft center of gravity control law based on sliding mode control. in AUS 2016 - 2016 IEEE/CSAA International Conference on Aircraft Utility Systems., 7748090, AUS 2016 - 2016 IEEE/CSAA International Conference on Aircraft Utility Systems, Institute of Electrical and Electronics Engineers Inc., pp. 438-442, 2016 IEEE/CSAA International Conference on Aircraft Utility Systems, AUS 2016, Beijing, China, 10/10/16. https://doi.org/10.1109/AUS.2016.7748090

Design of aircraft center of gravity control law based on sliding mode control. / Yan, Jianing; Zhang, Jing; Li, Haiquan.
AUS 2016 - 2016 IEEE/CSAA International Conference on Aircraft Utility Systems. Institute of Electrical and Electronics Engineers Inc., 2016. p. 438-442 7748090 (AUS 2016 - 2016 IEEE/CSAA International Conference on Aircraft Utility Systems).

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

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T1 - Design of aircraft center of gravity control law based on sliding mode control

AU - Yan, Jianing

AU - Zhang, Jing

AU - Li, Haiquan

PY - 2016/11/17

Y1 - 2016/11/17

N2 - A sliding mode based active center of gravity control law is designed for the aircraft with center of gravity varying during flight. As the basis, the general scheme of the active center of gravity control system is proposed, and the mathematic model of aircraft center of gravity varying with fuel transfer is established. Then, the center of gravity control law based on sliding mode control theory is designed, which can guarantee the control error converges to zero in finite time. Finally, simulations are carried out to verify the proposed method. Simulation results show that the sliding mode based center of gravity control law can accurately and rapidly track the given command for various different fuel transfer conditions.

AB - A sliding mode based active center of gravity control law is designed for the aircraft with center of gravity varying during flight. As the basis, the general scheme of the active center of gravity control system is proposed, and the mathematic model of aircraft center of gravity varying with fuel transfer is established. Then, the center of gravity control law based on sliding mode control theory is designed, which can guarantee the control error converges to zero in finite time. Finally, simulations are carried out to verify the proposed method. Simulation results show that the sliding mode based center of gravity control law can accurately and rapidly track the given command for various different fuel transfer conditions.

UR - https://www.scopus.com/pages/publications/85006754045

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DO - 10.1109/AUS.2016.7748090

M3 - 会议稿件

AN - SCOPUS:85006754045

T3 - AUS 2016 - 2016 IEEE/CSAA International Conference on Aircraft Utility Systems

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EP - 442

BT - AUS 2016 - 2016 IEEE/CSAA International Conference on Aircraft Utility Systems

PB - Institute of Electrical and Electronics Engineers Inc.

T2 - 2016 IEEE/CSAA International Conference on Aircraft Utility Systems, AUS 2016

Y2 - 10 October 2016 through 12 October 2016

ER -

Yan J, Zhang J, Li H. Design of aircraft center of gravity control law based on sliding mode control. In AUS 2016 - 2016 IEEE/CSAA International Conference on Aircraft Utility Systems. Institute of Electrical and Electronics Engineers Inc. 2016. p. 438-442. 7748090. (AUS 2016 - 2016 IEEE/CSAA International Conference on Aircraft Utility Systems). doi: 10.1109/AUS.2016.7748090

Design of aircraft center of gravity control law based on sliding mode control

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