Optimal low-cost transfer to L4 and L5 lagrangian points based on G-family of periodic orbits

Detalhes bibliográficos
Autor(a) principal: Salazar, Francisco
Data de Publicação: 2012
Outros Autores: Macau, Elbert E. N., De Melo, Cristiano F., Winter, Othon Cabo [UNESP]
Tipo de documento: Artigo de conferência
Idioma: eng
Título da fonte: Repositório Institucional da UNESP
Texto Completo: http://www.iafastro.net/iac/archive/browse/IAC-12/C1/7/15162/
http://hdl.handle.net/11449/73985
Resumo: An alternative transfer strategy to send spacecrafts to stable orbits around the Lagrangian equilibrium points L4 and L5 based in trajectories derived from the periodic orbits around LI is presented in this work. The trajectories derived, called Trajectories G, are described and studied in terms of the initial generation requirements and their energy variations relative to the Earth through the passage by the lunar sphere of influence. Missions for insertion of spacecrafts in elliptic orbits around L4 and L5 are analysed considering the Restricted Three-Body Problem Earth- Moon-particle and the results are discussed starting from the thrust, time of flight and energy variation relative to the Earth. Copyright© (2012) by the International Astronautical Federation.
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spelling Optimal low-cost transfer to L4 and L5 lagrangian points based on G-family of periodic orbitsEnergy variationsEquilibrium pointGeneration requirementsLagrangian pointsPeriodic orbitsRestricted three-body problemSphere of influencesTransfer strategiesLagrange multipliersSpacecraftTrajectoriesMoonAn alternative transfer strategy to send spacecrafts to stable orbits around the Lagrangian equilibrium points L4 and L5 based in trajectories derived from the periodic orbits around LI is presented in this work. The trajectories derived, called Trajectories G, are described and studied in terms of the initial generation requirements and their energy variations relative to the Earth through the passage by the lunar sphere of influence. Missions for insertion of spacecrafts in elliptic orbits around L4 and L5 are analysed considering the Restricted Three-Body Problem Earth- Moon-particle and the results are discussed starting from the thrust, time of flight and energy variation relative to the Earth. Copyright© (2012) by the International Astronautical Federation.National Institute for Space Research - INPE, Sao Jose dos Campos - SPUniversidade Federal do ABC, Rua Santa Adelia 166, Santo-Andre, SP, 09210-170Univ. Estadual Paulista - UNESP, Guaratingueta - SPUniv. Estadual Paulista - UNESP, Guaratingueta - SPInstituto Nacional de Pesquisas Espaciais (INPE)Universidade Federal do ABC (UFABC)Universidade Estadual Paulista (Unesp)Salazar, FranciscoMacau, Elbert E. N.De Melo, Cristiano F.Winter, Othon Cabo [UNESP]2014-05-27T11:27:23Z2014-05-27T11:27:23Z2012-12-01info:eu-repo/semantics/publishedVersioninfo:eu-repo/semantics/conferenceObject5919-5924http://www.iafastro.net/iac/archive/browse/IAC-12/C1/7/15162/Proceedings of the International Astronautical Congress, IAC, v. 7, p. 5919-5924.0074-1795http://hdl.handle.net/11449/739852-s2.0-8488351663609600245756472580000-0002-4901-3289Scopusreponame:Repositório Institucional da UNESPinstname:Universidade Estadual Paulista (UNESP)instacron:UNESPengProceedings of the International Astronautical Congress, IAC0,116info:eu-repo/semantics/openAccess2024-07-02T14:29:47Zoai:repositorio.unesp.br:11449/73985Repositório InstitucionalPUBhttp://repositorio.unesp.br/oai/requestopendoar:29462024-08-05T14:47:34.398557Repositório Institucional da UNESP - Universidade Estadual Paulista (UNESP)false
dc.title.none.fl_str_mv Optimal low-cost transfer to L4 and L5 lagrangian points based on G-family of periodic orbits
title Optimal low-cost transfer to L4 and L5 lagrangian points based on G-family of periodic orbits
spellingShingle Optimal low-cost transfer to L4 and L5 lagrangian points based on G-family of periodic orbits
Salazar, Francisco
Energy variations
Equilibrium point
Generation requirements
Lagrangian points
Periodic orbits
Restricted three-body problem
Sphere of influences
Transfer strategies
Lagrange multipliers
Spacecraft
Trajectories
Moon
title_short Optimal low-cost transfer to L4 and L5 lagrangian points based on G-family of periodic orbits
title_full Optimal low-cost transfer to L4 and L5 lagrangian points based on G-family of periodic orbits
title_fullStr Optimal low-cost transfer to L4 and L5 lagrangian points based on G-family of periodic orbits
title_full_unstemmed Optimal low-cost transfer to L4 and L5 lagrangian points based on G-family of periodic orbits
title_sort Optimal low-cost transfer to L4 and L5 lagrangian points based on G-family of periodic orbits
author Salazar, Francisco
author_facet Salazar, Francisco
Macau, Elbert E. N.
De Melo, Cristiano F.
Winter, Othon Cabo [UNESP]
author_role author
author2 Macau, Elbert E. N.
De Melo, Cristiano F.
Winter, Othon Cabo [UNESP]
author2_role author
author
author
dc.contributor.none.fl_str_mv Instituto Nacional de Pesquisas Espaciais (INPE)
Universidade Federal do ABC (UFABC)
Universidade Estadual Paulista (Unesp)
dc.contributor.author.fl_str_mv Salazar, Francisco
Macau, Elbert E. N.
De Melo, Cristiano F.
Winter, Othon Cabo [UNESP]
dc.subject.por.fl_str_mv Energy variations
Equilibrium point
Generation requirements
Lagrangian points
Periodic orbits
Restricted three-body problem
Sphere of influences
Transfer strategies
Lagrange multipliers
Spacecraft
Trajectories
Moon
topic Energy variations
Equilibrium point
Generation requirements
Lagrangian points
Periodic orbits
Restricted three-body problem
Sphere of influences
Transfer strategies
Lagrange multipliers
Spacecraft
Trajectories
Moon
description An alternative transfer strategy to send spacecrafts to stable orbits around the Lagrangian equilibrium points L4 and L5 based in trajectories derived from the periodic orbits around LI is presented in this work. The trajectories derived, called Trajectories G, are described and studied in terms of the initial generation requirements and their energy variations relative to the Earth through the passage by the lunar sphere of influence. Missions for insertion of spacecrafts in elliptic orbits around L4 and L5 are analysed considering the Restricted Three-Body Problem Earth- Moon-particle and the results are discussed starting from the thrust, time of flight and energy variation relative to the Earth. Copyright© (2012) by the International Astronautical Federation.
publishDate 2012
dc.date.none.fl_str_mv 2012-12-01
2014-05-27T11:27:23Z
2014-05-27T11:27:23Z
dc.type.status.fl_str_mv info:eu-repo/semantics/publishedVersion
dc.type.driver.fl_str_mv info:eu-repo/semantics/conferenceObject
format conferenceObject
status_str publishedVersion
dc.identifier.uri.fl_str_mv http://www.iafastro.net/iac/archive/browse/IAC-12/C1/7/15162/
Proceedings of the International Astronautical Congress, IAC, v. 7, p. 5919-5924.
0074-1795
http://hdl.handle.net/11449/73985
2-s2.0-84883516636
0960024575647258
0000-0002-4901-3289
url http://www.iafastro.net/iac/archive/browse/IAC-12/C1/7/15162/
http://hdl.handle.net/11449/73985
identifier_str_mv Proceedings of the International Astronautical Congress, IAC, v. 7, p. 5919-5924.
0074-1795
2-s2.0-84883516636
0960024575647258
0000-0002-4901-3289
dc.language.iso.fl_str_mv eng
language eng
dc.relation.none.fl_str_mv Proceedings of the International Astronautical Congress, IAC
0,116
dc.rights.driver.fl_str_mv info:eu-repo/semantics/openAccess
eu_rights_str_mv openAccess
dc.format.none.fl_str_mv 5919-5924
dc.source.none.fl_str_mv Scopus
reponame:Repositório Institucional da UNESP
instname:Universidade Estadual Paulista (UNESP)
instacron:UNESP
instname_str Universidade Estadual Paulista (UNESP)
instacron_str UNESP
institution UNESP
reponame_str Repositório Institucional da UNESP
collection Repositório Institucional da UNESP
repository.name.fl_str_mv Repositório Institucional da UNESP - Universidade Estadual Paulista (UNESP)
repository.mail.fl_str_mv
_version_ 1808128418164768768

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