Proceedings of the 2016 4th International Conference on Machinery, Materials and Computing Technology

Increasing damping ratio of high speed aircraft by terminal sliding mode method

Authors
Guangbin Wu, Guoqiang Liang
Corresponding Author
Guangbin Wu
Available Online March 2016.
DOI
https://doi.org/10.2991/icmmct-16.2016.12How to use a DOI?
Keywords
hypersonic aircraft; stability; control; free flying; numerical simulation
Abstract
A special method to increase damping ration of a kind of high speed vehicle was proposed by constructing a kind of terminal sliding mode surface. As the increase of damping ratio of flying system, the stability and stable margin can be greatly improved which is also a most important point cared by many aircraft designers. Although this kind of terminal method is not firstly proposed and is also not firstly applied in aircraft control, but it is mostly focused on the quickness point but not the damping ration. So this point is very new and although only simplified model is used to testify the rightness of proposed opinion, the detail simulation at last also can provide a strong foundation for the main conclusion.
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This is an open access article distributed under the CC BY-NC license.

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Volume Title
Proceedings of the 2016 4th International Conference on Machinery, Materials and Computing Technology
Series
Advances in Engineering Research
Publication Date
March 2016
ISBN
978-94-6252-165-0
ISSN
2352-5401
DOI
https://doi.org/10.2991/icmmct-16.2016.12How to use a DOI?
Open Access
This is an open access article distributed under the CC BY-NC license.

Cite this article

TY  - CONF
AU  - Guangbin Wu
AU  - Guoqiang Liang
PY  - 2016/03
DA  - 2016/03
TI  - Increasing damping ratio of high speed aircraft by terminal sliding mode method
BT  - Proceedings of the 2016 4th International Conference on Machinery, Materials and Computing Technology
PB  - Atlantis Press
SP  - 59
EP  - 64
SN  - 2352-5401
UR  - https://doi.org/10.2991/icmmct-16.2016.12
DO  - https://doi.org/10.2991/icmmct-16.2016.12
ID  - Wu2016/03
ER  -