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1. Identity statement
Reference TypeJournal Article
Sitemtc-m21b.sid.inpe.br
Holder Codeisadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S
Identifier8JMKD3MGP3W34P/3MRK398
Repositorysid.inpe.br/mtc-m21b/2016/11.22.19.40   (restricted access)
Last Update2016:11.22.19.40.29 (UTC) simone
Metadata Repositorysid.inpe.br/mtc-m21b/2016/11.22.19.40.29
Metadata Last Update2021:02.11.18.12.37 (UTC) administrator
DOI10.1007/s10569-016-9699-7
ISSN0923-2958
Citation KeyDeiennoMergPradSmir:2016:SaDeVi
TitleSatellite de-orbiting via controlled solar radiation pressure
Year2016
MonthNov.
Access Date2024, Apr. 24
Type of Workjournal article
Secondary TypePRE PI
Number of Files1
Size1055 KiB
2. Context
Author1 Deienno, Rogério
2 Merguizo Sanchez, Diogo
3 Prado, Antonio Fernando Bertachini de Almeida
4 Smirnov, Georgi
Resume Identifier1
2
3 8JMKD3MGP5W/3C9JGJA
Group1 DMC-ETE-INPE-MCTI-GOV-BR
2 DMC-ETE-INPE-MCTI-GOV-BR
3 DMC-ETE-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 University of Minho
Author e-Mail Address1 rogerio.deienno@inpe.br
2 diogo.sanchez@inpe.br
3 antonio.prado@inpe.br
JournalCelestial Mechanics and Dynamical Astronomy
Volume126
Number4
Pages433-459
Secondary MarkA2_ENGENHARIAS_III B1_INTERDISCIPLINAR B1_ASTRONOMIA_/_FÍSICA B2_MATEMÁTICA_/_PROBABILIDADE_E_ESTATÍSTICA B3_ENSINO B3_CIÊNCIA_DA_COMPUTAÇÃO
History (UTC)2016-11-22 19:40:29 :: simone -> administrator ::
2016-11-22 19:40:30 :: administrator -> simone :: 2016
2016-11-22 19:41:05 :: simone -> administrator :: 2016
2021-02-11 18:12:37 :: administrator -> simone :: 2016
3. Content and structure
Is the master or a copy?is the master
Content Stagecompleted
Transferable1
Content TypeExternal Contribution
Version Typepublisher
KeywordsAstrodynamics
Orbital maneuvers
Satellite de-orbiting
Solar radiation pressure
AbstractThe goal of the present research was to study the use of solar radiation pressure to place a satellite in an orbit that makes it to re-enter the atmosphere of the Earth. This phase of the mission is usual, since the orbital space around the Earth is crowded and all satellites have to be discarded after the end of their lifetimes. The technique proposed here is based on a device that can increase and decrease the area-to-mass ratio of the satellite when it is intended to reduce its altitude until a re-entry point is reached. Equations that predict the evolution of the eccentricity and semi-major axis of the orbit of the satellite are derived and can be used to allow the evaluation of the time required for the decay of the satellite. Numerical simulations are made, and they show the time required for the decay as a function of the area-to-mass ratio and the evolution of the most important orbital elements. The results show maps that indicate regions of fast decays as a function of the area-to-mass ratio and the initial inclination of the orbit of the satellite. They also confirmed the applicability of the equations derived here. The numerical results showed the role played by the evection and the Sun-synchronous resonances in the de-orbiting time.
AreaETES
Arrangementurlib.net > BDMCI > Fonds > Produção anterior à 2021 > DIDMC > Satellite de-orbiting via...
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4. Conditions of access and use
Languageen
Target FileDeienno_satellite.pdf
User Groupsimone
Reader Groupadministrator
simone
Visibilityshown
Archiving Policydenypublisher denyfinaldraft12
Read Permissiondeny from all and allow from 150.163
Update Permissionnot transferred
5. Allied materials
Mirror Repositoryurlib.net/www/2011/03.29.20.55
Next Higher Units8JMKD3MGPCW/446AF4B
Citing Item Listsid.inpe.br/bibdigital/2021/02.11.18.06 3
sid.inpe.br/mtc-m21/2012/07.13.14.40.20 1
DisseminationWEBSCI; PORTALCAPES.
Host Collectionsid.inpe.br/mtc-m21b/2013/09.26.14.25.20
6. Notes
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