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	Control strategy of optimal deployment for spacecraft solar array system with initial state uncertainty
	Ge, Xinsheng[1]; Yao, Qijia[2]; Chen, Liqun[3]
刊名	APPLIED MATHEMATICS AND MECHANICS-ENGLISH EDITION
	2018
卷号	39页码:1437-1452
关键词	optimal control trajectory tracking spacecraft solar array system two-point boundary value problem Legendre pseudospectral method (LPM) TP241 37N35 70E55 70F25
ISSN号	0253-4827
URL标识	查看原文
内容类型	期刊论文
URI标识	http://www.corc.org.cn/handle/1471x/2171822
专题	上海大学
作者单位	1.[1]Beijing Informat Sci & Technol Univ, Sch Mech & Elect Engn, Beijing 100192, Peoples R China. 2.[2]Beijing Informat Sci & Technol Univ, Sch Mech & Elect Engn, Beijing 100192, Peoples R China. 3.[3]Shanghai Univ, Shanghai Inst Appl Math & Mech, Shanghai 200072, Peoples R China.
推荐引用方式 GB/T 7714	Ge, Xinsheng[1],Yao, Qijia[2],Chen, Liqun[3]. Control strategy of optimal deployment for spacecraft solar array system with initial state uncertainty[J]. APPLIED MATHEMATICS AND MECHANICS-ENGLISH EDITION,2018,39:1437-1452.
APA	Ge, Xinsheng[1],Yao, Qijia[2],&Chen, Liqun[3].(2018).Control strategy of optimal deployment for spacecraft solar array system with initial state uncertainty.APPLIED MATHEMATICS AND MECHANICS-ENGLISH EDITION,39,1437-1452.
MLA	Ge, Xinsheng[1],et al."Control strategy of optimal deployment for spacecraft solar array system with initial state uncertainty".APPLIED MATHEMATICS AND MECHANICS-ENGLISH EDITION 39(2018):1437-1452.

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