A special kind of Optimal PID Control Method for High Speed Aircraft Attack Angle Tracking

DOI

10.2991/icmmcce-17.2017.151How to use a DOI?

Keywords

hypersonic aircraft; stability; PID control; optimal control; numerical simulation

Abstract

A new kind of optimal PID control method was proposed to solve the attack angle tracking problem of hypersonic aircraft . Both the control of attack angle and speed of aircraft are realized by the optimal PID control strategy. And a kind of integration of error method was used to mark the performance of system with different setting of PID parameters, also the adjustment rule is divided into two kinds of situation to guarantee the convergence of adjustment of PID parameters. At last, detailed numerical simulation is done to testify the rightness of the proposed method.

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  - Hui Wang
AU  - Junwei Lei
PY  - 2017/09
DA  - 2017/09
TI  - A special kind of Optimal PID Control Method for High Speed Aircraft Attack Angle Tracking
BT  - Proceedings of the 2017 5th International Conference on Mechatronics, Materials, Chemistry and Computer Engineering (ICMMCCE 2017)
PB  - Atlantis Press
SP  - 840
EP  - 844
SN  - 2352-5401
UR  - https://doi.org/10.2991/icmmcce-17.2017.151
DO  - 10.2991/icmmcce-17.2017.151
ID  - Wang2017/09
ER  -