A Simple Sliding Mode Control for Saucer-shaped Aircraft

DOI

10.2991/icmmct-17.2017.157How to use a DOI?

Keywords

Sliding Mode Control; Saucer-shaped Aircraft, Stability, Lyapunov function

Abstract

In this paper, a simple sliding mode control scheme, in which only the angular velocity and attitude angle have to be measured, is proposed to solve the non-minimum phase problem for a class of simplified linear model of saucer-shaped aircraft. The boundary of all closed-loop signals of the system is guaranteed by the selection and proof of the Lyapunov energy function. Finally, the simulation results show that the proposed method is correct and the control algorithm is simple and convenient.

Copyright

© 2017, 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  - LingLing Wang
AU  - HuaLi Wu
AU  - LiLi Yang
AU  - Junwei Lei
PY  - 2017/04
DA  - 2017/04
TI  - A Simple Sliding Mode Control for Saucer-shaped Aircraft
BT  - Proceedings of the 2017 5th International Conference on Machinery, Materials and Computing Technology (ICMMCT 2017)
PB  - Atlantis Press
SP  - 780
EP  - 783
SN  - 2352-5401
UR  - https://doi.org/10.2991/icmmct-17.2017.157
DO  - 10.2991/icmmct-17.2017.157
ID  - Wang2017/04
ER  -