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1. Identity statement
Reference TypeJournal Article
Siteplutao.sid.inpe.br
Holder Codeisadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S
Identifier8JMKD3MGP3W/3KN33Q8
Repositorysid.inpe.br/plutao/2015/12.04.13.49   (restricted access)
Last Update2015:12.10.11.13.24 (UTC) administrator
Metadata Repositorysid.inpe.br/plutao/2015/12.04.13.49.01
Metadata Last Update2021:07.28.22.22.43 (UTC) administrator
DOI10.1088/1742-6596/641/1/012027
ISSN1742-6588
Labellattes: 0088337156908774 1 Rocco:2015:GrDiGe
Citation KeyRocco:2015:GrDiGe
TitleGravitational disturbances generated by the Sun, Phobos and Deimos in orbital maneuvers around Mars with automatic correction of the semi-major axis
Year2015
Access Date2024, May 16
Type of Workconference paper
Secondary TypePRE PI
Number of Files1
Size1021 KiB
2. Context
AuthorRocco, Evandro Marconi
Resume Identifier8JMKD3MGP5W/3C9JH37
GroupDMC-ETE-INPE-MCTI-GOV-BR
AffiliationInstituto Nacional de Pesquisas Espaciais (INPE)
Author e-Mail Addressevandro.rocco@inpe.br
JournalJournal of Physics: Conference Series
Volume641
Pages012027
Secondary MarkB2_INTERDISCIPLINAR B2_ENGENHARIAS_III B3_MEDICINA_II B3_GEOCIÊNCIAS B4_MATERIAIS B4_ENGENHARIAS_II B4_BIOTECNOLOGIA C_QUÍMICA C_MATEMÁTICA_/_PROBABILIDADE_E_ESTATÍSTICA C_ENGENHARIAS_IV C_ECONOMIA C_ASTRONOMIA_/_FÍSICA
History (UTC)2015-12-04 13:49:01 :: lattes -> administrator ::
2021-07-28 22:22:43 :: administrator -> simone :: 2015
3. Content and structure
Is the master or a copy?is the master
Content Stagecompleted
Transferable1
Content TypeExternal Contribution
Version Typepublisher
KeywordsAstrodynamics
Orbital Maneuvers
Orbital Transfer
AbstractThe objective of this work is to analyze orbital maneuvers of a spacecraft orbiting Mars, considering disturbance effects due to the gravitational attraction of the Sun, Phobos and Deimos, beyond the disturbances due to the gravitational potential of Mars. To simulate the trajectory, constructive aspects of the propulsion system were considered. Initially ideal thrusters, capable of applying infinite magnitude of the thrust, were used. Thus, impulsive optimal maneuvers were obtained by scanning the solutions of the Lamberts problem in order to select the maneuver of minimum fuel consumption. Due to the impossibility of applying an impulse, the orbital maneuver must be distributed in a propulsive arc around the position of the impulse given by the solution of the Lamberts problem. However the effect of the propulsive arc is not exactly equivalent to the application of an impulse due to the errors in magnitude and direction of applied thrust. Therefore, the influence of the thrusters capacity in the trajectory was evaluated for a more realistic model instead of the ideal case represented by the impulsive approach. Beyond the evaluation of the deviation in the orbital path, was considered an automatic correction of the semi-major axis using continuous low thrust controlled in closed loop to minimize the error in the trajectory after the application of the main thrust.
AreaETES
Arrangementurlib.net > BDMCI > Fonds > Produção anterior à 2021 > DIDMC > Gravitational disturbances generated...
doc Directory Contentaccess
source Directory Contentthere are no files
agreement Directory Contentthere are no files
4. Conditions of access and use
Languagept
Target File1_rocco2.pdf
User Grouplattes
simone
Reader Groupadministrator
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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-m21/2012/07.13.14.45.41 1
DisseminationWEBSCI; PORTALCAPES; COMPENDEX; SCOPUS.
Host Collectiondpi.inpe.br/plutao@80/2008/08.19.15.01
6. Notes
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