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1. Identity statement
Reference TypeConference Paper (Conference Proceedings)
Sitemtc-m21b.sid.inpe.br
Holder Codeisadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S
Identifier8JMKD3MGP3W34P/3KH6HRB
Repositorysid.inpe.br/mtc-m21b/2015/11.04.14.57
Last Update2015:11.04.14.57.53 (UTC) administrator
Metadata Repositorysid.inpe.br/mtc-m21b/2015/11.04.14.57.33
Metadata Last Update2021:02.11.18.19.54 (UTC) administrator
Secondary KeyINPE--PRE/
Citation KeyRocco:2015:IOEuGa
TitleManeuvers around jupiter with automatic correction of the trajectory considering gravitational disturbances generated by the Galilean moons: IO, Europa Ganymede and Callisto
Year2015
Access Date2024, May 15
Secondary TypePRE CI
Number of Files1
Size512 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
Conference NameInternational Symposium on Space Flight Dynamics, 25
Conference LocationMunich, Germany
Date19-23 Oct.
Book TitleProceedings
History (UTC)2015-11-04 14:57:33 :: simone -> administrator ::
2021-02-11 18:19:54 :: administrator -> simone :: 2015
3. Content and structure
Is the master or a copy?is the master
Content Stagecompleted
Transferable1
Content TypeExternal Contribution
Version Typefinaldraft
KeywordsAstrodynamics
Orbital Maneuvers
Continuous Thrust
Automatic Correction
AbstractThe goal of this study is to evaluate the influence of the gravitational attraction of the Sun, and the Galilean moons, during orbital maneuvers of a spacecraft orbiting Jupiter. 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 Two Point Boundary Value Problem (TPBVP) for various values of transfer time in order to select the impulsive maneuver of minimum necessary velocity increment. Then, the selected maneuver was simulated considering a more realistic model of the propulsion system. In fact is not possible to accomplish an impulsive maneuver. Thus, the orbital maneuver must be distributed in a propulsive arc around the position of the impulse given by the solution of the TPBVP. In this arc was used a continuous thrust, limited to the capacity of the thrusters, with automatic correction of the trajectory. However the effect of the propulsive arc is not exactly equivalent to the application of an impulse. The evaluation of the difference between these approaches is extremely relevant in the mission analysis and spacecraft design of the trajectory control system. Therefore, the influence of the capacity of thrusters in the trajectory was evaluated for a more realistic model instead of the ideal case represented by the impulsive approach.
AreaETES
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4. Conditions of access and use
data URLhttp://mtc-m21b.sid.inpe.br/ibi/8JMKD3MGP3W34P/3KH6HRB
zipped data URLhttp://mtc-m21b.sid.inpe.br/zip/8JMKD3MGP3W34P/3KH6HRB
Languageen
User Groupsimone
Reader Groupadministrator
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Visibilityshown
Read Permissionallow from all
Update Permissionnot transferred
5. Allied materials
Mirror Repositoryurlib.net/www/2011/03.29.20.55
Next Higher Units8JMKD3MGPCW/446AF4B
Citing Item Listsid.inpe.br/mtc-m21/2012/07.13.14.45.41 4
sid.inpe.br/bibdigital@80/2006/04.07.15.50.13 1
Host Collectionsid.inpe.br/mtc-m21b/2013/09.26.14.25.20
6. Notes
Empty Fieldsarchivingpolicy archivist callnumber copyholder copyright creatorhistory descriptionlevel dissemination doi e-mailaddress edition editor format isbn issn label lineage mark nextedition notes numberofvolumes orcid organization pages parameterlist parentrepositories previousedition previouslowerunit progress project publisher publisheraddress rightsholder schedulinginformation secondarydate secondarymark serieseditor session shorttitle sponsor subject targetfile tertiarymark tertiarytype type url volume
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