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1. Identity statement
Reference TypeJournal Article
Sitemtc-m21d.sid.inpe.br
Holder Codeisadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S
Identifier8JMKD3MGP3W34T/46L45B2
Repositorysid.inpe.br/mtc-m21d/2022/04.04.13.39   (restricted access)
Last Update2022:04.04.13.39.31 (UTC) simone
Metadata Repositorysid.inpe.br/mtc-m21d/2022/04.04.13.39.31
Metadata Last Update2023:01.03.16.46.03 (UTC) administrator
DOI10.1038/s41598-022-08830-9
ISSN2045-2322
Citation KeyMurciaPiñerosPradDosSMora:2022:ApPeIn
TitleApplying the perturbative integral in aeromaneuvers around Mars to calculate the cost
Year2022
MonthDec.
Access Date2024, May 14
Type of Workjournal article
Secondary TypePRE PI
Number of Files1
Size3641 KiB
2. Context
Author1 Murcia Piñeros, Jhonathan O.
2 Prado, Antonio Fernando Bertachini de Almeida
3 Dos Santos, Walter Abrahão
4 Moraes, Rodolpho Vilhena de
Resume Identifier1
2 8JMKD3MGP5W/3C9JGJA
3 8JMKD3MGP5W/3C9JJC2
ORCID1 0000-0002-7013-6515
2 0000-0002-7966-3231
3 0000-0002-6516-6488
4 0000-0003-1289-8332
Group1
2 DIMEC-CGCE-INPE-MCTI-GOV-BR
3 DIPST-CGCE-INPE-MCTI-GOV-BR
Affiliation1 Universidade Federal de São Paulo (UNIFESP)
2 Instituto Nacional de Pesquisas Espaciais (INPE)
3 Instituto Nacional de Pesquisas Espaciais (INPE)
4 Universidade Federal de São Paulo (UNIFESP)
Author e-Mail Address1 jhonathan.pineros@unifesp.br
2 antonio.prado@inpe.br
3 walter.abrahao@inpe.br
JournalScientific Reports
Volume12
Number1
Pagese5022
Secondary MarkB2_BIODIVERSIDADE B3_ODONTOLOGIA B3_LETRAS_/_LINGUÍSTICA C_CIÊNCIAS_BIOLÓGICAS_III C_BIOTECNOLOGIA C_ASTRONOMIA_/_FÍSICA
History (UTC)2022-04-04 13:39:55 :: simone -> administrator :: 2022
2023-01-03 16:46:03 :: administrator -> simone :: 2022
3. Content and structure
Is the master or a copy?is the master
Content Stagecompleted
Transferable1
Content TypeExternal Contribution
Version Typepublisher
AbstractThe perturbative integral method was applied to quantify the contribution of external forces during a specific interval of time in trajectories of spacecraft around asteroids and under the Luni-solar influence. However, this method has not been used to quantify the contributions of drag in aerocapture and aerobraking. For this reason, the planet Mars is selected to apply this method during an aerogravity-assisted maneuver. Several trajectories are analyzed, making use of a drag device with area to mass ratios varying from 0.0 to 20.0 m2/kg, simulating solar sails or de-orbit devices. The mathematical model is based in the restricted three-body problem. The use of this maneuver makes it possible to obtain the variations of energy in the trajectory, replacing expensive maneuvers based on fuel consumption. To observe the effects of the maneuvers, different values of pericenter velocity and altitude were selected for prograde and retrograde orbits. The innovation of this research is the application of an integral method to quantify the delta-V of the aero gravity maneuver, comparing the cost of the maneuver with the traditional methods of space propulsion. The results allow the identification of orbits with conditions to capture, and the perturbative maps show the velocity variations.
AreaETES
Arrangementurlib.net > BDMCI > Fonds > Produção a partir de 2021 > CGCE > Applying the perturbative...
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Languageen
Target FileMurcia_2022_applying.pdf
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5. Allied materials
Next Higher Units8JMKD3MGPCW/46KTFK8
Citing Item Listsid.inpe.br/bibdigital/2022/04.03.17.52 3
sid.inpe.br/mtc-m21/2012/07.13.14.40.20 1
sid.inpe.br/mtc-m21/2012/07.13.15.01.48 1
DisseminationWEBSCI; PORTALCAPES; SCOPUS.
Host Collectionurlib.net/www/2021/06.04.03.40
6. Notes
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