The tracking control of hypersonic aircraft attack angle based on the coupling of elastic form and engines

DOI

10.2991/icmmita-15.2015.117How to use a DOI?

Keywords

hypersonic aircraft; stability; control; free flying; numerical simulation

Abstract

A kind of attack angle tracking controller with a former similar to PID control is proposed based on the pitch channel model of hypersonic aircraft released by America air force research center. Also the speed of the aircraft is controlled to tracking to a constant, which will make the system more stable and more easy to design a controller. At last, detailed numerical simulation is done to testify the rightness of the proposed method and the rightness of the hypersonic aircraft.

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  - Junwei Lei
AU  - Yuliang Chen
PY  - 2015/11
DA  - 2015/11
TI  - The tracking control of hypersonic aircraft attack angle based on the coupling of elastic form and engines
BT  - Proceedings of the 2015 3rd International Conference on Machinery, Materials and Information Technology Applications
PB  - Atlantis Press
SP  - 605
EP  - 609
SN  - 2352-538X
UR  - https://doi.org/10.2991/icmmita-15.2015.117
DO  - 10.2991/icmmita-15.2015.117
ID  - Lei2015/11
ER  -