文献
J-GLOBAL ID:201702234551025761
整理番号:17A2005747
ホーミング比例誘導則を用いたスピニングミサイルの安定性【Powered by NICT】
Stability of spinning missile with homing proportional guidance law
著者 (8件):
Hu Xiao
(School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, PR China)
,
Hu Xiao
(Key Laboratory of Dynamics and Control of Flight Vehicle, Ministry of Education, Beijing 100081, PR China)
,
Yang Shuxing
(School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, PR China)
,
Yang Shuxing
(Key Laboratory of Dynamics and Control of Flight Vehicle, Ministry of Education, Beijing 100081, PR China)
,
Xiong Fenfen
(School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, PR China)
,
Xiong Fenfen
(Key Laboratory of Dynamics and Control of Flight Vehicle, Ministry of Education, Beijing 100081, PR China)
,
Zhang Guoqing
(School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, PR China)
,
Zhang Guoqing
(Key Laboratory of Dynamics and Control of Flight Vehicle, Ministry of Education, Beijing 100081, PR China)
資料名:
Aerospace Science and Technology
(Aerospace Science and Technology)
巻:
71
ページ:
546-555
発行年:
2017年
JST資料番号:
W1580A
ISSN:
1270-9638
資料種別:
逐次刊行物 (A)
記事区分:
原著論文
発行国:
オランダ (NLD)
言語:
英語 (EN)