The research of open loop characteristics of lifting wing based on constant speed constant elastic cases

DOI

10.2991/icmmita-15.2015.118How to use a DOI?

Keywords

lift wing; open loop; stability; aircraft; actuator effect;

Abstract

The open loop response of lift wing is researched based on a kind of high speed vehicle model which is released by America air force research center. Since the speed of aircraft is too high, so its open loop response is unstable, which is difficult to do open loop actuator analysis with traditional method. In this paper, a kind of virtual flying conditions is assumed to make the simulation can last longer which can get more data to analysis the actuator effect, so the speed and elastic shape are considered to be constant. With the numerical simulation technology, the unstable open loop characteristics are recorded and analyzed.

Copyright

© 2015, 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  - Guoqiang Liang
AU  - Di Liu
PY  - 2015/11
DA  - 2015/11
TI  - The research of open loop characteristics of lifting wing based on constant speed constant elastic cases
BT  - Proceedings of the 2015 3rd International Conference on Machinery, Materials and Information Technology Applications
PB  - Atlantis Press
SP  - 610
EP  - 613
SN  - 2352-538X
UR  - https://doi.org/10.2991/icmmita-15.2015.118
DO  - 10.2991/icmmita-15.2015.118
ID  - Liang2015/11
ER  -