Indirect Optimization for Finite-Thrust Time-Optimal Orbital Maneuver

doi:10.2514/1.44885

CORC > 北京大学 > 工学院

	Indirect Optimization for Finite-Thrust Time-Optimal Orbital Maneuver
	Yue, Xincheng ; Yang, Ying ; Geng, Zhiyong
刊名	journal of guidance control and dynamics
	2010
关键词	SATELLITE
DOI	10.2514/1.44885
英文摘要	The optimal-time orbital maneuver problems for the cases of the transfer, intercept, and rendezvous under a unified framework using the modified equinoctial elements are discussed. Transfer starts from a prescribed initial motion and ends at a prescribed final motion such as orbit-to-orbit and intercept starts from a prescribed or a partially prescribed initial condition and ends at a partially prescribed final condition such as from a circular orbit to a specified radius. The orbital intercept problem should be considered under the conditions that the relative position of two satellites is zero while the relative velocity is free at the terminal time. The two satellites are called the interceptor and the target, respectively, and the target is supposed to move on a fixed orbit without thrust. The relative position and the relative velocity are required to be zero at the terminal time for the orbital rendezvous problem.; http://gateway.webofknowledge.com/gateway/Gateway.cgi?GWVersion=2&SrcApp=PARTNER_APP&SrcAuth=LinksAMR&KeyUT=WOS:000275802200032&DestLinkType=FullRecord&DestApp=ALL_WOS&UsrCustomerID=8e1609b174ce4e31116a60747a720701 ; Engineering, Aerospace; Instruments & Instrumentation; SCI(E); EI; 4; ARTICLE; 2; 628-634; 33
语种	英语
内容类型	期刊论文
源URL	[http://ir.pku.edu.cn/handle/20.500.11897/316078]
专题	工学院
推荐引用方式 GB/T 7714	Yue, Xincheng,Yang, Ying,Geng, Zhiyong. Indirect Optimization for Finite-Thrust Time-Optimal Orbital Maneuver[J]. journal of guidance control and dynamics,2010.
APA	Yue, Xincheng,Yang, Ying,&Geng, Zhiyong.(2010).Indirect Optimization for Finite-Thrust Time-Optimal Orbital Maneuver.journal of guidance control and dynamics.
MLA	Yue, Xincheng,et al."Indirect Optimization for Finite-Thrust Time-Optimal Orbital Maneuver".journal of guidance control and dynamics (2010).