Research on free flying of high speed aircraft without control
Aijun Zhou, Haibo Wang, Junbo Chu, Tianwei Li, Guoqiang Liang
Available Online November 2015.
- 10.2991/icmmita-15.2015.109How to use a DOI?
- aircraft; stability; control; free flying; numerical simulation
The research is based on a kind of pitch channel hypersonic aircraft model built is released by USA air force, adopting the digital simulation to verify the basic free flight state preliminarily. The difference of the stability and divergent could get observation through the simulation result between hypersonic aircraft’s attitude and attack angle and the traditional low supersonic aircraft. The research is aimed at evaluate the rationality of models, and do the preliminary analysis of the dynamic characteristics of 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 - Aijun Zhou AU - Haibo Wang AU - Junbo Chu AU - Tianwei Li AU - Guoqiang Liang PY - 2015/11 DA - 2015/11 TI - Research on free flying of high speed aircraft without control BT - Proceedings of the 2015 3rd International Conference on Machinery, Materials and Information Technology Applications PB - Atlantis Press SP - 568 EP - 571 SN - 2352-538X UR - https://doi.org/10.2991/icmmita-15.2015.109 DO - 10.2991/icmmita-15.2015.109 ID - Zhou2015/11 ER -