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Reference TypeJournal Article
Sitemtc-m21d.sid.inpe.br
Holder Codeisadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S
Identifier8JMKD3MGP3W34T/45LSHJS
Repositorysid.inpe.br/mtc-m21d/2021/10.25.14.37   (restricted access)
Last Update2021:11.25.13.42.47 (UTC) simone
Metadatasid.inpe.br/mtc-m21d/2021/10.25.14.37.01
Metadata Last Update2021:11.25.13.42.48 (UTC) simone
ISSN1220-5168;
2285-3758
Citation KeyAljbaaeMePrSoTeNeMa:2021:FiApSp
TitleFirst approximation for spacecraft motion relative to (99942) Apophis
Year2021
Access Date2021, Dec. 04
Type of Workjournal article
Secondary TypePRE PI
Number of Files1
Size9892 KiB
Context area
Author1 Aljbaae, Safwan
2 Merguizo Sanchez, Diogo
3 Prado, Antonio Fernando Bertachini de Almeida
4 Souchay, Jean
5 Terra, Maisa O.
6 Negri, Rodolfo Batista
7 Marchi, Luis Otávio
Resume Identifier1
2
3 8JMKD3MGP5W/3C9JGJA
Group1 DIMEC-CGCE-INPE-MCTI-GOV-BR
2 DIMEC-CGCE-INPE-MCTI-GOV-BR
3 DIMEC-CGCE-INPE-MCTI-GOV-BR
4
5
6 CMC-ETES-DIPGR-INPE-MCTI-GOV-BR
7 CMC-ETES-DIPGR-INPE-MCTI-GOV-BR
Affiliation1 Instituto Nacional de Pesquisas Espaciais (INPE)
2 Instituto Nacional de Pesquisas Espaciais (INPE)
3 Instituto Nacional de Pesquisas Espaciais (INPE)
4 Universitè Paris
5 Instituto Tecnológico de Aeronáutica (ITA)
6 Instituto Nacional de Pesquisas Espaciais (INPE)
7 Instituto Nacional de Pesquisas Espaciais (INPE)
Author e-Mail Address1 safwan.aljbaae@gmail.com
2 sanchezfisica@gmail.com
3 antonio.prado@inpe.br
4
5
6 rodolfobnegri@yahoo.com.br
7 marchi.luis@yahoo.com.br
JournalRomanian Astronomical Journal
Volume31
Number3
Pages241-263
History (UTC)2021-10-25 14:37:39 :: simone -> administrator :: 2021
2021-11-05 11:42:33 :: administrator -> simone :: 2021
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Is the master or a copy?is the master
Content Stagecompleted
Transferable1
Content TypeExternal Contribution
Version Typepublisher
KeywordsCelestial MechanicsDynamical astronomyMinor planetsasteroids: individual (Apophis)
AbstractWe aim at providing a preliminary approach on the dynamics of a spacecraft in orbit about the asteroid (99942) Apophis during its Earth close approach. The physical properties from the polyhedral shape of the target are derived by assigning each tetrahedron to a point mass in its center. That considerably reduces the computation processing time compared to previous methods to evaluate the gravitational potential. The surfaces of section close to Apophis are build considering or not the gravitational perturbations of the Sun, the planets, and the SRP. The Earth is the one that most affects the investigated region making the vast majority of the orbits collide or escape from the system. Moreover, from numerical analysis of orbits started on March 1, 2029, the less perturbed region is characterized by the variation of the semimajor axis of 40-day orbits, which do not exceed 2 km very close to the central body (a < 4 km, e < 0.4). However, no regions investigated could be a possible option for inserting a spacecraft into natural orbits around Apophis during the close approach with our planet. Finally, to solve the stabilization problem in the system, we apply a robust path following control law to control the orbital geometry of a spacecraft. At last, we present an example of a successful operation of our orbit control with a total Delta v of 0.495 m/s for 60 days. All our results are gathered in the CPM-ASTEROID database, which will be regularly updated by considering other asteroids.
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Languageen
Target FileFIRSTAPPROXIMATIONFORSPACECRAFTMOTIONRELATIVETO99942APOPHIS.pdf
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simone
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Update Permissionnot transferred
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Mirror Repositoryurlib.net/www/2021/06.04.03.40.25
DisseminationWEBSCI; SCOPUS.
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