Orbit determination using gps including perturbations due to geopotential coefficients of high degree and order and solar radiation pressure
Autor(a) principal: | |
---|---|
Data de Publicação: | 2008 |
Outros Autores: | , |
Tipo de documento: | Artigo de conferência |
Idioma: | eng |
Título da fonte: | Repositório Institucional da UNESP |
Texto Completo: | http://hdl.handle.net/11449/231859 |
Resumo: | The main target here is to determine the orbit of an artificial satellite, using signals of the GPS constellation and least squares algorithms implemented through sequential Givens rotations as a method of estimation, with the aim of improving the performance of the orbit estimation process and, at the same time, minimizing the computational procedure cost. Geopotential perturbations up to high order and direct solar radiation pressure were taken into account. It was also considered the position of the GPS antenna on the satellite body that, lately, consists of the influence of the satellite attitude motion in the orbit determination process. An application has been done, using real data from the Topex/Poseidon satellite, whose ephemeris is available at Internet. The best accuracy obtained in position was smaller than 5 meters for short period (2 hours) and smaller than 28 meters for long period (24 hours) orbit determination. In both cases, the perturbations mentioned before were taken into consideration and the analysis occurred without selective availability on the signals measurements. |
id |
UNSP_bef68191f693e1d25e60001305e7d676 |
---|---|
oai_identifier_str |
oai:repositorio.unesp.br:11449/231859 |
network_acronym_str |
UNSP |
network_name_str |
Repositório Institucional da UNESP |
repository_id_str |
2946 |
spelling |
Orbit determination using gps including perturbations due to geopotential coefficients of high degree and order and solar radiation pressureThe main target here is to determine the orbit of an artificial satellite, using signals of the GPS constellation and least squares algorithms implemented through sequential Givens rotations as a method of estimation, with the aim of improving the performance of the orbit estimation process and, at the same time, minimizing the computational procedure cost. Geopotential perturbations up to high order and direct solar radiation pressure were taken into account. It was also considered the position of the GPS antenna on the satellite body that, lately, consists of the influence of the satellite attitude motion in the orbit determination process. An application has been done, using real data from the Topex/Poseidon satellite, whose ephemeris is available at Internet. The best accuracy obtained in position was smaller than 5 meters for short period (2 hours) and smaller than 28 meters for long period (24 hours) orbit determination. In both cases, the perturbations mentioned before were taken into consideration and the analysis occurred without selective availability on the signals measurements.UNESP, Guaratingueta - SPINPE - Sao Jose dos Campos, SPUNESP, Guaratingueta - SPUniversidade Estadual Paulista (UNESP)INPE - Sao Jose dos CamposMoraes, Rodolpho Vilhena De [UNESP]Raimundo, Paula Cristiane P.Kuga, Helio K.2022-04-29T08:47:50Z2022-04-29T08:47:50Z2008-12-01info:eu-repo/semantics/publishedVersioninfo:eu-repo/semantics/conferenceObject923-933Advances in the Astronautical Sciences, v. 130 PART 1, p. 923-933.0065-3438http://hdl.handle.net/11449/2318592-s2.0-60349098949Scopusreponame:Repositório Institucional da UNESPinstname:Universidade Estadual Paulista (UNESP)instacron:UNESPengAdvances in the Astronautical Sciencesinfo:eu-repo/semantics/openAccess2024-07-02T14:29:47Zoai:repositorio.unesp.br:11449/231859Repositório InstitucionalPUBhttp://repositorio.unesp.br/oai/requestopendoar:29462024-07-02T14:29:47Repositório Institucional da UNESP - Universidade Estadual Paulista (UNESP)false |
dc.title.none.fl_str_mv |
Orbit determination using gps including perturbations due to geopotential coefficients of high degree and order and solar radiation pressure |
title |
Orbit determination using gps including perturbations due to geopotential coefficients of high degree and order and solar radiation pressure |
spellingShingle |
Orbit determination using gps including perturbations due to geopotential coefficients of high degree and order and solar radiation pressure Moraes, Rodolpho Vilhena De [UNESP] |
title_short |
Orbit determination using gps including perturbations due to geopotential coefficients of high degree and order and solar radiation pressure |
title_full |
Orbit determination using gps including perturbations due to geopotential coefficients of high degree and order and solar radiation pressure |
title_fullStr |
Orbit determination using gps including perturbations due to geopotential coefficients of high degree and order and solar radiation pressure |
title_full_unstemmed |
Orbit determination using gps including perturbations due to geopotential coefficients of high degree and order and solar radiation pressure |
title_sort |
Orbit determination using gps including perturbations due to geopotential coefficients of high degree and order and solar radiation pressure |
author |
Moraes, Rodolpho Vilhena De [UNESP] |
author_facet |
Moraes, Rodolpho Vilhena De [UNESP] Raimundo, Paula Cristiane P. Kuga, Helio K. |
author_role |
author |
author2 |
Raimundo, Paula Cristiane P. Kuga, Helio K. |
author2_role |
author author |
dc.contributor.none.fl_str_mv |
Universidade Estadual Paulista (UNESP) INPE - Sao Jose dos Campos |
dc.contributor.author.fl_str_mv |
Moraes, Rodolpho Vilhena De [UNESP] Raimundo, Paula Cristiane P. Kuga, Helio K. |
description |
The main target here is to determine the orbit of an artificial satellite, using signals of the GPS constellation and least squares algorithms implemented through sequential Givens rotations as a method of estimation, with the aim of improving the performance of the orbit estimation process and, at the same time, minimizing the computational procedure cost. Geopotential perturbations up to high order and direct solar radiation pressure were taken into account. It was also considered the position of the GPS antenna on the satellite body that, lately, consists of the influence of the satellite attitude motion in the orbit determination process. An application has been done, using real data from the Topex/Poseidon satellite, whose ephemeris is available at Internet. The best accuracy obtained in position was smaller than 5 meters for short period (2 hours) and smaller than 28 meters for long period (24 hours) orbit determination. In both cases, the perturbations mentioned before were taken into consideration and the analysis occurred without selective availability on the signals measurements. |
publishDate |
2008 |
dc.date.none.fl_str_mv |
2008-12-01 2022-04-29T08:47:50Z 2022-04-29T08:47:50Z |
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 |
Advances in the Astronautical Sciences, v. 130 PART 1, p. 923-933. 0065-3438 http://hdl.handle.net/11449/231859 2-s2.0-60349098949 |
identifier_str_mv |
Advances in the Astronautical Sciences, v. 130 PART 1, p. 923-933. 0065-3438 2-s2.0-60349098949 |
url |
http://hdl.handle.net/11449/231859 |
dc.language.iso.fl_str_mv |
eng |
language |
eng |
dc.relation.none.fl_str_mv |
Advances in the Astronautical Sciences |
dc.rights.driver.fl_str_mv |
info:eu-repo/semantics/openAccess |
eu_rights_str_mv |
openAccess |
dc.format.none.fl_str_mv |
923-933 |
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_ |
1803649371381694464 |