The fuel consumption analysis for satellite formation reconfiguration based on three-impulsive approach

Currently micro/nano satellites have become the protagonists in most formation flying missions, and there is an urgent demand to propose a reliable approach for quick fuel estimation of multiple-impulsive scheme on-board to achieve formation reconfiguration problems. This paper presents an optimal c...

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Autores principales:	Xingchuan Liu, Danhe Chen, Wenhe Liao, Kunxu Wu
Formato:	article
Lenguaje:	EN
Publicado:	Elsevier 2021
Materias:	Satellite formation reconfiguration Relative motion equation Three-impulsive approach Optimal impulsive scheme Combinational method Electrical engineering. Electronics. Nuclear engineering TK1-9971
Acceso en línea:	https://doaj.org/article/ad2ad97ce14f4435bb021692d622f2f9
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spelling	oai:doaj.org-article:ad2ad97ce14f4435bb021692d622f2f92021-11-26T04:34:10ZThe fuel consumption analysis for satellite formation reconfiguration based on three-impulsive approach2352-484710.1016/j.egyr.2021.08.117https://doaj.org/article/ad2ad97ce14f4435bb021692d622f2f92021-11-01T00:00:00Zhttp://www.sciencedirect.com/science/article/pii/S2352484721007198https://doaj.org/toc/2352-4847Currently micro/nano satellites have become the protagonists in most formation flying missions, and there is an urgent demand to propose a reliable approach for quick fuel estimation of multiple-impulsive scheme on-board to achieve formation reconfiguration problems. This paper presents an optimal control approach based on multiple impulses for satellite formation in-plane reconfiguration issue in near circular orbit. Based on initial small deviation in the cylindrical coordinates system, a relative orbit motion expression is investigated, and a time-varying propagate system without perturbation is presented in this paper, which is suitable to calculate the solution of relative orbital maneuver by multiple impulses. The formation reconfiguration problem of this relative orbit motion is considered, and orbital motion equations with initial deviations are presented for relative orbital transfer calculation. Through different combinations of method from normal four-impulsive solution, the optimal three-impulsive method for relative orbital transfer in plane is obtained by analysis solution based on graphical and numerical way. In the end of paper, the effectivity and optimality of method is validated, and fuel consumption is analyzed through simulations of assumptive different formation reconfiguration missions.Xingchuan LiuDanhe ChenWenhe LiaoKunxu WuElsevierarticleSatellite formation reconfigurationRelative motion equationThree-impulsive approachOptimal impulsive schemeCombinational methodElectrical engineering. Electronics. Nuclear engineeringTK1-9971ENEnergy Reports, Vol 7, Iss , Pp 65-77 (2021)
institution	DOAJ
collection	DOAJ
language	EN
topic	Satellite formation reconfiguration Relative motion equation Three-impulsive approach Optimal impulsive scheme Combinational method Electrical engineering. Electronics. Nuclear engineering TK1-9971
spellingShingle	Satellite formation reconfiguration Relative motion equation Three-impulsive approach Optimal impulsive scheme Combinational method Electrical engineering. Electronics. Nuclear engineering TK1-9971 Xingchuan Liu Danhe Chen Wenhe Liao Kunxu Wu The fuel consumption analysis for satellite formation reconfiguration based on three-impulsive approach
description	Currently micro/nano satellites have become the protagonists in most formation flying missions, and there is an urgent demand to propose a reliable approach for quick fuel estimation of multiple-impulsive scheme on-board to achieve formation reconfiguration problems. This paper presents an optimal control approach based on multiple impulses for satellite formation in-plane reconfiguration issue in near circular orbit. Based on initial small deviation in the cylindrical coordinates system, a relative orbit motion expression is investigated, and a time-varying propagate system without perturbation is presented in this paper, which is suitable to calculate the solution of relative orbital maneuver by multiple impulses. The formation reconfiguration problem of this relative orbit motion is considered, and orbital motion equations with initial deviations are presented for relative orbital transfer calculation. Through different combinations of method from normal four-impulsive solution, the optimal three-impulsive method for relative orbital transfer in plane is obtained by analysis solution based on graphical and numerical way. In the end of paper, the effectivity and optimality of method is validated, and fuel consumption is analyzed through simulations of assumptive different formation reconfiguration missions.
format	article
author	Xingchuan Liu Danhe Chen Wenhe Liao Kunxu Wu
author_facet	Xingchuan Liu Danhe Chen Wenhe Liao Kunxu Wu
author_sort	Xingchuan Liu
title	The fuel consumption analysis for satellite formation reconfiguration based on three-impulsive approach
title_short	The fuel consumption analysis for satellite formation reconfiguration based on three-impulsive approach
title_full	The fuel consumption analysis for satellite formation reconfiguration based on three-impulsive approach
title_fullStr	The fuel consumption analysis for satellite formation reconfiguration based on three-impulsive approach
title_full_unstemmed	The fuel consumption analysis for satellite formation reconfiguration based on three-impulsive approach
title_sort	fuel consumption analysis for satellite formation reconfiguration based on three-impulsive approach
publisher	Elsevier
publishDate	2021
url	https://doaj.org/article/ad2ad97ce14f4435bb021692d622f2f9
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The fuel consumption analysis for satellite formation reconfiguration based on three-impulsive approach

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