Increasing damping ratio of high speed aircraft by terminal sliding mode method

DOI

10.2991/icmmct-16.2016.12How to use a DOI?

Keywords

hypersonic aircraft; stability; control; free flying; numerical simulation

Abstract

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.

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/).

Download article (PDF)

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  -