The Research on EHA Based Aircraft Braking System and Its Nonlinear Control

DOI

10.2991/acta-14.2014.5How to use a DOI?

Keywords

aircraft braking system; electro-hydrostatic actuator; antiskid control; fuzzy PID control

Abstract

An Electro-hydrostatic actuator (EHA) structure with joint of pump control and valve control is proposed for more electric aircraft (MEA) braking system, the working principle of the system is analyzed, and on the basis of that, the mathematical models of the system components are established. To compromise the problem of pressure overshoot and dynamic characteristics with the conventional PID control method, and to prevent wheels from mistakenly locking which resulting in decreased brake efficiency, a fuzzy PID pressure controller is designed. Through simulation test, the rated pressure step response time of the system is about 0.35 s with 2 percent overshoot and 0.05 MPa steady-state error, the system -3 dB bandwidth is 8 Hz. It is demonstrated that the structure is feasible, the controller design is reasonable, and the EHA can satisfy the requirements of the aircraft braking system in static and dynamic performance.

Copyright

© 2014, 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  - Li Bingqiang
AU  - Xing Hualing
PY  - 2014/06
DA  - 2014/06
TI  - The Research on EHA Based Aircraft Braking System and Its Nonlinear Control
BT  - 2014 International Conference on Automatic Control Theory and Application
PB  - Atlantis Press
SP  - 18
EP  - 22
SN  - 2352-5398
UR  - https://doi.org/10.2991/acta-14.2014.5
DO  - 10.2991/acta-14.2014.5
ID  - Bingqiang2014/06
ER  -