Flight test of fault-tolerant flight control system using simple adaptive control with PID controller
Aircraft Engineering and Aerospace Technology
ISSN: 0002-2667
Article publication date: 2 January 2018
Abstract
Purpose
This paper aims to demonstrate the effectiveness of a fault-tolerant flight control method by using simple adaptive control (SAC) with PID controller.
Design/methodology/approach
Numerical simulations and flight tests are executed for pitch angle and roll angle control of research aircraft MuPAL-α under the following fault cases: sudden reduction in aileron effectiveness, sudden reduction in elevator effectiveness and loss of longitudinal static stability.
Findings
The simulations and flight tests reveal the effectiveness of the proposed SAC with PID controller as a fault-tolerant flight controller.
Practical implications
This research includes implications for the development of vehicles’ robustness.
Originality/value
This study proposes novel SAC-based flight controller and actually demonstrates the effectiveness by flight test.
Keywords
Acknowledgements
The authors would like to express their deepest gratitude to Mr Tomoaki Hosoya (JAXA), whose support was invaluable during the flight test. This work was supported by JSPS Grant-in-Aid for Scientific Research (B); Grant Number 26289321.
Citation
Matsuki, H., Nishiyama, T., Omori, Y., Suzuki, S., Masui, K. and Sato, M. (2018), "Flight test of fault-tolerant flight control system using simple adaptive control with PID controller", Aircraft Engineering and Aerospace Technology, Vol. 90 No. 1, pp. 210-218. https://doi.org/10.1108/AEAT-03-2016-0052
Publisher
:Emerald Publishing Limited
Copyright © 2018, Emerald Publishing Limited