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

Integral Sliding Mode Control of Airship Pitch Channel simplified model

Authors
Aijun Zhou, Junbo Chu, Haibo Wang, Tianwei Li, Guoqiang Liang
Corresponding Author
Aijun Zhou
Available Online March 2016.
DOI
https://doi.org/10.2991/icmmct-16.2016.9How to use a DOI?
Keywords
hypersonic aircraft; stability; control; free flying; numerical simulation
Abstract
A kind of integral type sliding mode control law was designed for a kind of simplified pitch channel model of hypersonic aircraft which is widely discussed recently. The advantage of sliding mode control is that it has strong robustness. And the integral sliding mode control method can reduce steady state error. And with the help of constructing two Lyapunov functions, all signals of close system are proved to be stable. At last, detailed simulation was done to testify the rightness of the proposed method.
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Proceedings
2016 4th International Conference on Machinery, Materials and Computing Technology
Part of 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-16.2016.9How 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  - Aijun Zhou
AU  - Junbo Chu
AU  - Haibo Wang
AU  - Tianwei Li
AU  - Guoqiang Liang
PY  - 2016/03
DA  - 2016/03
TI  - Integral Sliding Mode Control of Airship Pitch Channel simplified model
BT  - 2016 4th International Conference on Machinery, Materials and Computing Technology
PB  - Atlantis Press
SP  - 43
EP  - 47
SN  - 2352-5401
UR  - https://doi.org/10.2991/icmmct-16.2016.9
DO  - https://doi.org/10.2991/icmmct-16.2016.9
ID  - Zhou2016/03
ER  -