Studying the lifetime of orbits around Moons in elliptic motion
Autor(a) principal: | |
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Data de Publicação: | 2016 |
Outros Autores: | |
Tipo de documento: | Artigo |
Idioma: | eng |
Título da fonte: | Repositório Institucional da UNESP |
Texto Completo: | http://dx.doi.org/10.1007/s40314-015-0258-8 http://hdl.handle.net/11449/178316 |
Resumo: | The main goal of the present paper is to study the lifetime of orbits around moons that are in elliptic motion around their parent planet. The lifetime of the orbits is defined as the time the orbit stays in orbit around the moon without colliding with its surface. The mathematical model used to solve this problem is the second order expansion of the potential of the disturbing planet, assumed to be in an elliptical orbit. The results are presented in maps showing the lifetime of the orbit as a function of its initial inclination and eccentricity. The only perturbation acting on the orbit of the spacecraft is assumed to be the gravity of the planet, so the problem is solved by studying the orbital evolution of the spacecraft perturbed by a third body in an elliptical orbit. The region of inclination above the critical value of the third-body perturbation (around 63∘) is studied, since below that value the orbits survive for a long time. The influence of the eccentricity of the primaries is also investigated, assuming a hypothetical system that has the same mass parameter and sizes of the Earth–Moon system, but the eccentricity can be in the range 0.0–0.2. |
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Repositório Institucional da UNESP |
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Studying the lifetime of orbits around Moons in elliptic motionAstrodynamicsAveraged methodsStability of orbitsThird-body perturbationThe main goal of the present paper is to study the lifetime of orbits around moons that are in elliptic motion around their parent planet. The lifetime of the orbits is defined as the time the orbit stays in orbit around the moon without colliding with its surface. The mathematical model used to solve this problem is the second order expansion of the potential of the disturbing planet, assumed to be in an elliptical orbit. The results are presented in maps showing the lifetime of the orbit as a function of its initial inclination and eccentricity. The only perturbation acting on the orbit of the spacecraft is assumed to be the gravity of the planet, so the problem is solved by studying the orbital evolution of the spacecraft perturbed by a third body in an elliptical orbit. The region of inclination above the critical value of the third-body perturbation (around 63∘) is studied, since below that value the orbits survive for a long time. The influence of the eccentricity of the primaries is also investigated, assuming a hypothetical system that has the same mass parameter and sizes of the Earth–Moon system, but the eccentricity can be in the range 0.0–0.2.UNESP Univ. Estadual Paulista (UNESP)UNESP Univ. Estadual PaulistaUNESP Univ. Estadual Paulista (UNESP)UNESP Univ. Estadual PaulistaUniversidade Estadual Paulista (Unesp)Gomes, Vivian Martins [UNESP]de C�ssia Domingos, Rita [UNESP]2018-12-11T17:29:45Z2018-12-11T17:29:45Z2016-10-01info:eu-repo/semantics/publishedVersioninfo:eu-repo/semantics/article653-661application/pdfhttp://dx.doi.org/10.1007/s40314-015-0258-8Computational and Applied Mathematics, v. 35, n. 3, p. 653-661, 2016.1807-03020101-8205http://hdl.handle.net/11449/17831610.1007/s40314-015-0258-82-s2.0-849898722812-s2.0-84989872281.pdfScopusreponame:Repositório Institucional da UNESPinstname:Universidade Estadual Paulista (UNESP)instacron:UNESPengComputational and Applied Mathematics0,272info:eu-repo/semantics/openAccess2024-07-02T14:29:31Zoai:repositorio.unesp.br:11449/178316Repositório InstitucionalPUBhttp://repositorio.unesp.br/oai/requestopendoar:29462024-08-05T21:44:35.963139Repositório Institucional da UNESP - Universidade Estadual Paulista (UNESP)false |
dc.title.none.fl_str_mv |
Studying the lifetime of orbits around Moons in elliptic motion |
title |
Studying the lifetime of orbits around Moons in elliptic motion |
spellingShingle |
Studying the lifetime of orbits around Moons in elliptic motion Gomes, Vivian Martins [UNESP] Astrodynamics Averaged methods Stability of orbits Third-body perturbation |
title_short |
Studying the lifetime of orbits around Moons in elliptic motion |
title_full |
Studying the lifetime of orbits around Moons in elliptic motion |
title_fullStr |
Studying the lifetime of orbits around Moons in elliptic motion |
title_full_unstemmed |
Studying the lifetime of orbits around Moons in elliptic motion |
title_sort |
Studying the lifetime of orbits around Moons in elliptic motion |
author |
Gomes, Vivian Martins [UNESP] |
author_facet |
Gomes, Vivian Martins [UNESP] de C�ssia Domingos, Rita [UNESP] |
author_role |
author |
author2 |
de C�ssia Domingos, Rita [UNESP] |
author2_role |
author |
dc.contributor.none.fl_str_mv |
Universidade Estadual Paulista (Unesp) |
dc.contributor.author.fl_str_mv |
Gomes, Vivian Martins [UNESP] de C�ssia Domingos, Rita [UNESP] |
dc.subject.por.fl_str_mv |
Astrodynamics Averaged methods Stability of orbits Third-body perturbation |
topic |
Astrodynamics Averaged methods Stability of orbits Third-body perturbation |
description |
The main goal of the present paper is to study the lifetime of orbits around moons that are in elliptic motion around their parent planet. The lifetime of the orbits is defined as the time the orbit stays in orbit around the moon without colliding with its surface. The mathematical model used to solve this problem is the second order expansion of the potential of the disturbing planet, assumed to be in an elliptical orbit. The results are presented in maps showing the lifetime of the orbit as a function of its initial inclination and eccentricity. The only perturbation acting on the orbit of the spacecraft is assumed to be the gravity of the planet, so the problem is solved by studying the orbital evolution of the spacecraft perturbed by a third body in an elliptical orbit. The region of inclination above the critical value of the third-body perturbation (around 63∘) is studied, since below that value the orbits survive for a long time. The influence of the eccentricity of the primaries is also investigated, assuming a hypothetical system that has the same mass parameter and sizes of the Earth–Moon system, but the eccentricity can be in the range 0.0–0.2. |
publishDate |
2016 |
dc.date.none.fl_str_mv |
2016-10-01 2018-12-11T17:29:45Z 2018-12-11T17:29:45Z |
dc.type.status.fl_str_mv |
info:eu-repo/semantics/publishedVersion |
dc.type.driver.fl_str_mv |
info:eu-repo/semantics/article |
format |
article |
status_str |
publishedVersion |
dc.identifier.uri.fl_str_mv |
http://dx.doi.org/10.1007/s40314-015-0258-8 Computational and Applied Mathematics, v. 35, n. 3, p. 653-661, 2016. 1807-0302 0101-8205 http://hdl.handle.net/11449/178316 10.1007/s40314-015-0258-8 2-s2.0-84989872281 2-s2.0-84989872281.pdf |
url |
http://dx.doi.org/10.1007/s40314-015-0258-8 http://hdl.handle.net/11449/178316 |
identifier_str_mv |
Computational and Applied Mathematics, v. 35, n. 3, p. 653-661, 2016. 1807-0302 0101-8205 10.1007/s40314-015-0258-8 2-s2.0-84989872281 2-s2.0-84989872281.pdf |
dc.language.iso.fl_str_mv |
eng |
language |
eng |
dc.relation.none.fl_str_mv |
Computational and Applied Mathematics 0,272 |
dc.rights.driver.fl_str_mv |
info:eu-repo/semantics/openAccess |
eu_rights_str_mv |
openAccess |
dc.format.none.fl_str_mv |
653-661 application/pdf |
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_ |
1808129352907358208 |