Relative State Transition Matrix Using Geometric Approach for Onboard Implementation

Detalhes bibliográficos
Autor(a) principal: Ramachandran,Mankali P.
Data de Publicação: 2017
Tipo de documento: Artigo
Idioma: eng
Título da fonte: Journal of Aerospace Technology and Management (Online)
Texto Completo: http://old.scielo.br/scielo.php?script=sci_arttext&pid=S2175-91462017000300328
Resumo: ABSTRACT In the present study relative state transition matrix was obtained. It matches the relative motion of 2 satellites while including the oblate perturbation. The used formulation applies the geometric approach and is in Cartesian frame. The relative state transition matrix uses absolute state transition matrix of individual satellites. Thereon, simplification in computing methods and on-board implementation at controls are explored in a leader/follower coordination method. Numerical experiments illustrate the accuracy when the baseline separation is equal to 2 km and eccentricity is 0.005 and 0.05 for all the inclinations.
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spelling Relative State Transition Matrix Using Geometric Approach for Onboard ImplementationState transition matrixFormation flyingOrbitOblateABSTRACT In the present study relative state transition matrix was obtained. It matches the relative motion of 2 satellites while including the oblate perturbation. The used formulation applies the geometric approach and is in Cartesian frame. The relative state transition matrix uses absolute state transition matrix of individual satellites. Thereon, simplification in computing methods and on-board implementation at controls are explored in a leader/follower coordination method. Numerical experiments illustrate the accuracy when the baseline separation is equal to 2 km and eccentricity is 0.005 and 0.05 for all the inclinations.Departamento de Ciência e Tecnologia Aeroespacial2017-09-01info:eu-repo/semantics/articleinfo:eu-repo/semantics/publishedVersiontext/htmlhttp://old.scielo.br/scielo.php?script=sci_arttext&pid=S2175-91462017000300328Journal of Aerospace Technology and Management v.9 n.3 2017reponame:Journal of Aerospace Technology and Management (Online)instname:Departamento de Ciência e Tecnologia Aeroespacial (DCTA)instacron:DCTA10.5028/jatm.v9i3.762info:eu-repo/semantics/openAccessRamachandran,Mankali P.eng2017-08-18T00:00:00Zoai:scielo:S2175-91462017000300328Revistahttp://www.jatm.com.br/ONGhttps://old.scielo.br/oai/scielo-oai.php||secretary@jatm.com.br2175-91461984-9648opendoar:2017-08-18T00:00Journal of Aerospace Technology and Management (Online) - Departamento de Ciência e Tecnologia Aeroespacial (DCTA)false
dc.title.none.fl_str_mv Relative State Transition Matrix Using Geometric Approach for Onboard Implementation
title Relative State Transition Matrix Using Geometric Approach for Onboard Implementation
spellingShingle Relative State Transition Matrix Using Geometric Approach for Onboard Implementation
Ramachandran,Mankali P.
State transition matrix
Formation flying
Orbit
Oblate
title_short Relative State Transition Matrix Using Geometric Approach for Onboard Implementation
title_full Relative State Transition Matrix Using Geometric Approach for Onboard Implementation
title_fullStr Relative State Transition Matrix Using Geometric Approach for Onboard Implementation
title_full_unstemmed Relative State Transition Matrix Using Geometric Approach for Onboard Implementation
title_sort Relative State Transition Matrix Using Geometric Approach for Onboard Implementation
author Ramachandran,Mankali P.
author_facet Ramachandran,Mankali P.
author_role author
dc.contributor.author.fl_str_mv Ramachandran,Mankali P.
dc.subject.por.fl_str_mv State transition matrix
Formation flying
Orbit
Oblate
topic State transition matrix
Formation flying
Orbit
Oblate
description ABSTRACT In the present study relative state transition matrix was obtained. It matches the relative motion of 2 satellites while including the oblate perturbation. The used formulation applies the geometric approach and is in Cartesian frame. The relative state transition matrix uses absolute state transition matrix of individual satellites. Thereon, simplification in computing methods and on-board implementation at controls are explored in a leader/follower coordination method. Numerical experiments illustrate the accuracy when the baseline separation is equal to 2 km and eccentricity is 0.005 and 0.05 for all the inclinations.
publishDate 2017
dc.date.none.fl_str_mv 2017-09-01
dc.type.driver.fl_str_mv info:eu-repo/semantics/article
dc.type.status.fl_str_mv info:eu-repo/semantics/publishedVersion
format article
status_str publishedVersion
dc.identifier.uri.fl_str_mv http://old.scielo.br/scielo.php?script=sci_arttext&pid=S2175-91462017000300328
url http://old.scielo.br/scielo.php?script=sci_arttext&pid=S2175-91462017000300328
dc.language.iso.fl_str_mv eng
language eng
dc.relation.none.fl_str_mv 10.5028/jatm.v9i3.762
dc.rights.driver.fl_str_mv info:eu-repo/semantics/openAccess
eu_rights_str_mv openAccess
dc.format.none.fl_str_mv text/html
dc.publisher.none.fl_str_mv Departamento de Ciência e Tecnologia Aeroespacial
publisher.none.fl_str_mv Departamento de Ciência e Tecnologia Aeroespacial
dc.source.none.fl_str_mv Journal of Aerospace Technology and Management v.9 n.3 2017
reponame:Journal of Aerospace Technology and Management (Online)
instname:Departamento de Ciência e Tecnologia Aeroespacial (DCTA)
instacron:DCTA
instname_str Departamento de Ciência e Tecnologia Aeroespacial (DCTA)
instacron_str DCTA
institution DCTA
reponame_str Journal of Aerospace Technology and Management (Online)
collection Journal of Aerospace Technology and Management (Online)
repository.name.fl_str_mv Journal of Aerospace Technology and Management (Online) - Departamento de Ciência e Tecnologia Aeroespacial (DCTA)
repository.mail.fl_str_mv ||secretary@jatm.com.br
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