Increasing damping ratio of high speed aircraft by terminal sliding mode method
Guangbin Wu, Guoqiang Liang
Available Online March 2016.
- 10.2991/icmmct-16.2016.12How to use a DOI?
- hypersonic aircraft; stability; control; free flying; numerical simulation
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.
- © 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 - 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 - 10.2991/icmmct-16.2016.12 ID - Wu2016/03 ER -