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1. Identity statement
Reference TypeJournal Article
Sitemtc-m21c.sid.inpe.br
Holder Codeisadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S
Identifier8JMKD3MGP3W34R/42LA6JE
Repositorysid.inpe.br/mtc-m21c/2020/06.10.15.29   (restricted access)
Last Update2020:06.10.15.29.53 (UTC) simone
Metadata Repositorysid.inpe.br/mtc-m21c/2020/06.10.15.29.53
Metadata Last Update2022:01.04.01.35.12 (UTC) administrator
DOI10.1140/epjst/e2020-900144-9
ISSN1951-6355
Citation KeyMurciaPiñerosGomeDosSGole:2020:EfRoSp
TitleEffects of the rotation of a spacecraft in an atmospheric close approach with the Earth
Year2020
MonthMay
Access Date2024, May 02
Type of Workjournal article
Secondary TypePRE PI
Number of Files1
Size1828 KiB
2. Context
Author1 Murcia Piñeros, Jhonathan Orlando
2 Gomes, Vivian Martins
3 Dos Santos, Walter Abrahão
4 Golebiewska, Justyna
Resume Identifier1
2
3 8JMKD3MGP5W/3C9JJC2
Group1 DIDEA-CGETE-INPE-MCTIC-GOV-BR
2
3 DIDEA-CGETE-INPE-MCTIC-GOV-BR
Affiliation1 Instituto Nacional de Pesquisas Espaciais (INPE)
2 Universidade Estadual Paulista (UNESP)
3 Instituto Nacional de Pesquisas Espaciais (INPE)
4 Adam Mickiewicz University
Author e-Mail Address1 jhonathan.pineros@inpe.br
2 vivianmartinsgomes@gmail.com
3 walter.abrahao@inpe.br
JournalEuropean Physical Journal Special Topics
Volume229
Number8
Pages1517-1526
History (UTC)2020-06-10 15:30:26 :: simone -> administrator :: 2020
2022-01-04 01:35:12 :: administrator -> simone :: 2020
3. Content and structure
Is the master or a copy?is the master
Content Stagecompleted
Transferable1
Content TypeExternal Contribution
Version Typepublisher
AbstractA 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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4. Conditions of access and use
Languageen
Target Filemurica_effects.pdf
User Groupsimone
Reader Groupadministrator
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Visibilityshown
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5. Allied materials
Next Higher Units8JMKD3MGPCW/3F6GF6B
Citing Item Listsid.inpe.br/mtc-m21/2012/07.13.15.01.48 1
sid.inpe.br/bibdigital/2013/11.04.22.00 1
DisseminationPORTALCAPES; SCOPUS.
Host Collectionurlib.net/www/2017/11.22.19.04
6. Notes
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