A kind of differential sliding mode controller design for pitch channel simplified model of hypersonic aircraft

DOI

10.2991/icmmct-16.2016.11How to use a DOI?

Keywords

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

Abstract

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.

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  - 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  -