A Simple Fuzzy Backstepping Integral Compound Control Method for Saucer-shaped Aircraft

DOI

10.2991/icmmct-17.2017.170How to use a DOI?

Keywords

Fuzzy; Backstepping; Integral; Saucer-shaped Aircraft

Abstract

In order to solve the problem of insufficient output stability accuracy of saucer-shaped aircraft with simplified non-minimum phase linear model, a fuzzy backstepping and integral compound method is designed based on the fuzzy backstepping control by measuring the attitude angle and angular velocity of the aircraft. By means of Lyapunov function, the stability of all closed-loop signals of the whole system is proved. Finally, the numerical simulation shows that the proposed method is correct, but the output has a certain oscillation and overshoot, and the overshoot is caused by improper gain matching due to the backstepping control, while the introduction of the integration also increased the oscillation to some extent.

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/).

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TY  - CONF
AU  - Yuqiang Jin
AU  - YuLiang Chen
AU  - Junwei Lei
PY  - 2017/04
DA  - 2017/04
TI  - A Simple Fuzzy Backstepping Integral Compound Control Method for Saucer-shaped Aircraft
BT  - Proceedings of the 2017 5th International Conference on Machinery, Materials and Computing Technology (ICMMCT 2017)
PB  - Atlantis Press
SP  - 845
EP  - 849
SN  - 2352-5401
UR  - https://doi.org/10.2991/icmmct-17.2017.170
DO  - 10.2991/icmmct-17.2017.170
ID  - Jin2017/04
ER  -