A kind of differential sliding mode controller design for pitch channel simplified model of hypersonic aircraft
Guoqiang Liang, Guangbin Wu
Available Online March 2016.
- 10.2991/icmmct-16.2016.11How to use a DOI?
- hypersonic aircraft; stability; control; free flying; numerical simulation
A kind of differential type sliding mode control law was proposed to improve the robustness of 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 differential item which can provide a special damping for flying system. With the increasing of damping ratio, the stable margin of the who flying system can be greatly increased. Also, to prove the stability of the whole system, two Lyapunov functions were constructed and all signals of close system are proved to be stable. At last, detailed simulation was done to testify the effectiveness 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 - Guoqiang Liang AU - Guangbin Wu PY - 2016/03 DA - 2016/03 TI - A kind of differential sliding mode controller design for pitch channel simplified model of hypersonic aircraft BT - Proceedings of the 2016 4th International Conference on Machinery, Materials and Computing Technology PB - Atlantis Press SP - 53 EP - 58 SN - 2352-5401 UR - https://doi.org/10.2991/icmmct-16.2016.11 DO - 10.2991/icmmct-16.2016.11 ID - Liang2016/03 ER -