Effects of the rotation of a spacecraft in an atmospheric close approach with the Earth
Autor(a) principal: | |
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Data de Publicação: | 2020 |
Outros Autores: | , , |
Tipo de documento: | Artigo |
Idioma: | eng |
Título da fonte: | Repositório Institucional da UNESP |
Texto Completo: | http://dx.doi.org/10.1140/epjst/e2020-900144-9 http://hdl.handle.net/11449/201821 |
Resumo: | A maneuver called “Aerogravity Assisted” is known in the literature to increase the energy gains given by a close approach between a spacecraft and a planet using the atmosphere of the planet. Several previous papers showed the importance of this topic in different aspects. The present paper has the goal of studying the effects of the spacecraft rotation in this maneuver. This rotation implies in a variable ballistic coefficient and this fact can change the results of the maneuver. Several masses, sizes and angular velocities will be tested and the effects of these parameters will be measured. The dynamical model considers the atmosphere of the Earth, in terms of drag, the gravitational fields of the Earth and the Sun, assumed to be points of mass, and the rotating spacecraft. The Earth and the Sun are assumed to be in circular coplanar orbits around their common center of mass. The equations of motion are the ones given by the circular planar restricted three-body problem with the addition of the forces generated by the atmospheric drag. The primary objective is to map the energy variations of the spacecraft orbits due to this close approach as a function of the spacecraft angular velocity. This rotation can be used as control of the maneuver to try to reach different goals. |
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Repositório Institucional da UNESP |
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Effects of the rotation of a spacecraft in an atmospheric close approach with the EarthA maneuver called “Aerogravity Assisted” is known in the literature to increase the energy gains given by a close approach between a spacecraft and a planet using the atmosphere of the planet. Several previous papers showed the importance of this topic in different aspects. The present paper has the goal of studying the effects of the spacecraft rotation in this maneuver. This rotation implies in a variable ballistic coefficient and this fact can change the results of the maneuver. Several masses, sizes and angular velocities will be tested and the effects of these parameters will be measured. The dynamical model considers the atmosphere of the Earth, in terms of drag, the gravitational fields of the Earth and the Sun, assumed to be points of mass, and the rotating spacecraft. The Earth and the Sun are assumed to be in circular coplanar orbits around their common center of mass. The equations of motion are the ones given by the circular planar restricted three-body problem with the addition of the forces generated by the atmospheric drag. The primary objective is to map the energy variations of the spacecraft orbits due to this close approach as a function of the spacecraft angular velocity. This rotation can be used as control of the maneuver to try to reach different goals.Space Electronics Division Instituto Nacional de Pesquisas EspaciaisUNESP Universidade Estadual PaulistaFaculty of Physics Astronomical Observatory Institute Adam Mickiewicz UniversityUNESP Universidade Estadual PaulistaInstituto Nacional de Pesquisas EspaciaisUniversidade Estadual Paulista (Unesp)Adam Mickiewicz UniversityMurcia Piñeros, Jhonathan O.Gomes, Vivian Martins [UNESP]dos Santos, Walter AbrahãoGolebiewska, Justyna2020-12-12T02:42:42Z2020-12-12T02:42:42Z2020-05-01info:eu-repo/semantics/publishedVersioninfo:eu-repo/semantics/article1517-1526http://dx.doi.org/10.1140/epjst/e2020-900144-9European Physical Journal: Special Topics, v. 229, n. 8, p. 1517-1526, 2020.1951-64011951-6355http://hdl.handle.net/11449/20182110.1140/epjst/e2020-900144-92-s2.0-85085582002Scopusreponame:Repositório Institucional da UNESPinstname:Universidade Estadual Paulista (UNESP)instacron:UNESPengEuropean Physical Journal: Special Topicsinfo:eu-repo/semantics/openAccess2024-07-02T14:29:20Zoai:repositorio.unesp.br:11449/201821Repositório InstitucionalPUBhttp://repositorio.unesp.br/oai/requestopendoar:29462024-07-02T14:29:20Repositório Institucional da UNESP - Universidade Estadual Paulista (UNESP)false |
dc.title.none.fl_str_mv |
Effects of the rotation of a spacecraft in an atmospheric close approach with the Earth |
title |
Effects of the rotation of a spacecraft in an atmospheric close approach with the Earth |
spellingShingle |
Effects of the rotation of a spacecraft in an atmospheric close approach with the Earth Murcia Piñeros, Jhonathan O. |
title_short |
Effects of the rotation of a spacecraft in an atmospheric close approach with the Earth |
title_full |
Effects of the rotation of a spacecraft in an atmospheric close approach with the Earth |
title_fullStr |
Effects of the rotation of a spacecraft in an atmospheric close approach with the Earth |
title_full_unstemmed |
Effects of the rotation of a spacecraft in an atmospheric close approach with the Earth |
title_sort |
Effects of the rotation of a spacecraft in an atmospheric close approach with the Earth |
author |
Murcia Piñeros, Jhonathan O. |
author_facet |
Murcia Piñeros, Jhonathan O. Gomes, Vivian Martins [UNESP] dos Santos, Walter Abrahão Golebiewska, Justyna |
author_role |
author |
author2 |
Gomes, Vivian Martins [UNESP] dos Santos, Walter Abrahão Golebiewska, Justyna |
author2_role |
author author author |
dc.contributor.none.fl_str_mv |
Instituto Nacional de Pesquisas Espaciais Universidade Estadual Paulista (Unesp) Adam Mickiewicz University |
dc.contributor.author.fl_str_mv |
Murcia Piñeros, Jhonathan O. Gomes, Vivian Martins [UNESP] dos Santos, Walter Abrahão Golebiewska, Justyna |
description |
A maneuver called “Aerogravity Assisted” is known in the literature to increase the energy gains given by a close approach between a spacecraft and a planet using the atmosphere of the planet. Several previous papers showed the importance of this topic in different aspects. The present paper has the goal of studying the effects of the spacecraft rotation in this maneuver. This rotation implies in a variable ballistic coefficient and this fact can change the results of the maneuver. Several masses, sizes and angular velocities will be tested and the effects of these parameters will be measured. The dynamical model considers the atmosphere of the Earth, in terms of drag, the gravitational fields of the Earth and the Sun, assumed to be points of mass, and the rotating spacecraft. The Earth and the Sun are assumed to be in circular coplanar orbits around their common center of mass. The equations of motion are the ones given by the circular planar restricted three-body problem with the addition of the forces generated by the atmospheric drag. The primary objective is to map the energy variations of the spacecraft orbits due to this close approach as a function of the spacecraft angular velocity. This rotation can be used as control of the maneuver to try to reach different goals. |
publishDate |
2020 |
dc.date.none.fl_str_mv |
2020-12-12T02:42:42Z 2020-12-12T02:42:42Z 2020-05-01 |
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/10.1140/epjst/e2020-900144-9 European Physical Journal: Special Topics, v. 229, n. 8, p. 1517-1526, 2020. 1951-6401 1951-6355 http://hdl.handle.net/11449/201821 10.1140/epjst/e2020-900144-9 2-s2.0-85085582002 |
url |
http://dx.doi.org/10.1140/epjst/e2020-900144-9 http://hdl.handle.net/11449/201821 |
identifier_str_mv |
European Physical Journal: Special Topics, v. 229, n. 8, p. 1517-1526, 2020. 1951-6401 1951-6355 10.1140/epjst/e2020-900144-9 2-s2.0-85085582002 |
dc.language.iso.fl_str_mv |
eng |
language |
eng |
dc.relation.none.fl_str_mv |
European Physical Journal: Special Topics |
dc.rights.driver.fl_str_mv |
info:eu-repo/semantics/openAccess |
eu_rights_str_mv |
openAccess |
dc.format.none.fl_str_mv |
1517-1526 |
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 |
|
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1803649959308820480 |