An Optimized Flight Control System of Quad-rotor Aircraft

DOI

10.2991/icmemtc-16.2016.198How to use a DOI?

Keywords

optimization;csyncretic data of gyroscope; accelerometer and magnetometer;fuzzy algorithm;joint simulation

Abstract

The flight performance of four-rotor unmanned helicopter depends largely on the flight control system, the flight control system was mainly consisted of attitude algorithm and controller. During design time, firstly, in order to real-time update for the quaternion , we fused the data of gyroscope accelerometer and magnetometer. And we obtained the attitude angle through quaternion to Euler angle conversion. Then, we calculated the output of throttle by fuzzy algorithm, which was used to control the attitude. And control algorithm was used and optimized by the method of the joint simulation. Finally, four-rotor unmanned helicopter was connected to PC with bluetooth and we obtained the air data of UAV form PC. The data display that the fuzzy controller can keep the stability of flying

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  - Xiaoning Chen
AU  - Hongting Dong
AU  - Dexiang Zhang
AU  - Jing Xia
PY  - 2016/04
DA  - 2016/04
TI  - An Optimized Flight Control System of Quad-rotor Aircraft
BT  - Proceedings of the 2016 3rd International Conference on Materials Engineering, Manufacturing Technology and Control
PB  - Atlantis Press
SP  - 1000
EP  - 1003
SN  - 2352-5401
UR  - https://doi.org/10.2991/icmemtc-16.2016.198
DO  - 10.2991/icmemtc-16.2016.198
ID  - Chen2016/04
ER  -