The research on open loop actuator response of high speed vehicle based on constant speed and constant elasticity

DOI

10.2991/icmmita-15.2015.115How to use a DOI?

Keywords

high speed vehicle; open loop; actuator response; virtual flying; stability

Abstract

Based on a kind of pitch channel model of supersonic aircraft which is released by America air force research center, a kind of open loop testing method is proposed to testify the actuator effect of a kind of high speed aircraft. The difference between this type of aircraft and other traditional aircraft is that open loop response is unstable so it is not easy to do this kind of actuator test. So a kind of virtual flying condition is assumed to make the simulation can last for a longer time, also it can make the analysis of actuator effect to be more clear and simple. Also the physical meanings of this kind of unstable open loop response is 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  - Yong Liu
AU  - Yongbing Chen
AU  - Wenkui Li
AU  - Jianhong Shi
PY  - 2015/11
DA  - 2015/11
TI  - The research on open loop actuator response of high speed vehicle based on constant speed and constant elasticity
BT  - Proceedings of the 2015 3rd International Conference on Machinery, Materials and Information Technology Applications
PB  - Atlantis Press
SP  - 595
EP  - 599
SN  - 2352-538X
UR  - https://doi.org/10.2991/icmmita-15.2015.115
DO  - 10.2991/icmmita-15.2015.115
ID  - Liu2015/11
ER  -