Integral Sliding Mode Control of Airship Pitch Channel simplified model
Aijun Zhou, Junbo Chu, Haibo Wang, Tianwei Li, Guoqiang Liang
Available Online March 2016.
- 10.2991/icmmct-16.2016.9How to use a DOI?
- hypersonic aircraft; stability; control; free flying; numerical simulation
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.
- © 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/).
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 - 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 -