The tracking control of hypersonic aircraft attack angle based on the coupling of elastic form and engines
- 10.2991/icmmita-15.2015.117How to use a DOI?
- hypersonic aircraft; stability; control; free flying; numerical simulation
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.
- © 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/).
Cite this article
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 -