The Analysis And The Research Of The Helicopter PIO

DOI

10.2991/jimec-17.2017.113How to use a DOI?

Keywords

pilot induced coupling; flight control system; the stability analysis.

Abstract

Closed-loop analysis method is proposed for pilot induced coupling with helicopter flight control system in closed loop. Combining with the longitudinal identification model of a certain helicopter, McRuer pilot model, designed stability augmentation system and frequency domain model are established for pilot induced coupling analysis. By combining the basic analytical methods of the classical automatic control theory and the actual backgrounds, the properties of the root locus, the characteristics of the time domain and the frequency domain are studied. The properties as well as the reasons of the PIO are also analyzed in comparison. Meanwhile, feasible measures to improve the PIO are discussed considering the controller design and pilot's manipulation. Results show that the analysis method proposed can not only reveal the physical nature of PIO qualitatively, but also quantitatively. The analysis has theoretical reference significance in both flight control system design and pilot's manipulation applications. In the designing process of modern helicopter, high gain as well as broad band FCS has been an important target of the advantaged helicopter

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  - Penghui Xu
AU  - Yanqiu Ju
AU  - Chi Qi
AU  - Yue Wang
PY  - 2017/10
DA  - 2017/10
TI  - The Analysis And The Research Of The Helicopter PIO
BT  - Proceedings of the 2017 2nd Joint International Information Technology, Mechanical and Electronic Engineering Conference (JIMEC 2017)
PB  - Atlantis Press
SP  - 522
EP  - 529
SN  - 2352-538X
UR  - https://doi.org/10.2991/jimec-17.2017.113
DO  - 10.2991/jimec-17.2017.113
ID  - Xu2017/10
ER  -