Integral Sliding Mode Control of Airship Pitch Channel simplified model

DOI

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.

Copyright

© 2016, the Authors. Published by Atlantis Press.

Open Access

This is an open access article distributed under the CC BY-NC license (http://creativecommons.org/licenses/by-nc/4.0/).

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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  - Proceedings of the 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  - 10.2991/icmmct-16.2016.9
ID  - Zhou2016/03
ER  -