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1. Identity statement
Reference TypeJournal Article
Sitemtc-m21c.sid.inpe.br
Holder Codeisadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S
Identifier8JMKD3MGP3W34R/3SFTNLB
Repositorysid.inpe.br/mtc-m21c/2019/01.02.16.09
Last Update2019:01.02.16.09.10 (UTC) simone
Metadata Repositorysid.inpe.br/mtc-m21c/2019/01.02.16.09.10
Metadata Last Update2021:02.11.18.10.48 (UTC) administrator
ISSN1984-9648
Citation KeyMotaNivaRoccSchl:2018:TrOpLa
TitleTrajectory optimization of launch vehicles using object-oriented programming
Year2018
Access Date2024, May 15
Type of Workjournal article
Secondary TypePRE PN
Number of Files1
Size1939 KiB
2. Context
Author1 Mota, Fábio Antônio da Silva
2 Nivaldo, Hinckel José
3 Rocco, Evandro Marconi
4 Schlingloff, Hanfried
Resume Identifier1
2
3 8JMKD3MGP5W/3C9JH37
ORCID1 0000-0003-3672-0547
2 0000-0002-0171-2697
3 0000-0003-0660-0587
4 0000-0003-1806-9113
Group1
2 DIDMC-CGETE-INPE-MCTIC-GOV-BR
3 DIDMC-CGETE-INPE-MCTIC-GOV-BR
Affiliation1 Universidade Federal do ABC (UFABC)
2 Instituto Nacional de Pesquisas Espaciais (INPE)
3 Instituto Nacional de Pesquisas Espaciais (INPE)
4 Ostbayerische Technische Hochschule Regensburg
Author e-Mail Address1
2
3 evandro.rocco@inpe.br
JournalJournal of Aerospace Technology and Management
Volume10
Pagese3918
Secondary MarkB2_PLANEJAMENTO_URBANO_E_REGIONAL_/_DEMOGRAFIA B3_INTERDISCIPLINAR B4_GEOCIÊNCIAS B4_ENGENHARIAS_II B4_CIÊNCIAS_AMBIENTAIS B5_ENGENHARIAS_IV B5_ENGENHARIAS_III B5_CIÊNCIA_DA_COMPUTAÇÃO C_ASTRONOMIA_/_FÍSICA
History (UTC)2019-01-02 16:09:10 :: simone -> administrator ::
2019-01-02 16:09:11 :: administrator -> simone :: 2018
2019-01-02 16:09:48 :: simone -> administrator :: 2018
2021-02-11 18:10:48 :: administrator -> simone :: 2018
3. Content and structure
Is the master or a copy?is the master
Content Stagecompleted
Transferable1
Content TypeExternal Contribution
Version Typepublisher
KeywordsLaunch vehicle
Trajectory
Optimization
Object-oriented programming
AbstractThe aim of this study is to model launch vehicles with focus on 3-DOF trajectory optimization using a modular approach. Despite the large number of operational launch vehicles, they usually consist of basic components and subsystems. In other words, a launch vehicle is an assembly of stages, which in turn is divided into propellant system and engine, and the engine is an assembly of basic components such as pumps, turbines, combustion chamber, and nozzle. To allow future extension and reuse of the codes, a modular structure using object-oriented programming is used. Two formulations of state equations of the trajectory and two optimization methods are described. The launch vehicle performance will be measured by payload mass for a given mission. The simulations of the VLS-1, Ariane 5 and VLS-Alfa were performed and showed good agreement with the literature.
AreaETES
Arrangementurlib.net > BDMCI > Fonds > Produção anterior à 2021 > DIDMC > Trajectory optimization of...
doc Directory Contentaccess
source Directory Contentthere are no files
agreement Directory Content
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4. Conditions of access and use
data URLhttp://urlib.net/ibi/8JMKD3MGP3W34R/3SFTNLB
zipped data URLhttp://urlib.net/zip/8JMKD3MGP3W34R/3SFTNLB
Languageen
Target Filemota_trajectory.pdf
User Groupsimone
Reader Groupadministrator
simone
Visibilityshown
Archiving Policyallowpublisher allowfinaldraft
Update Permissionnot transferred
5. Allied materials
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 2
DisseminationWEBSCI; PORTALCAPES; COMPENDEX; SCOPUS.
Host Collectionurlib.net/www/2017/11.22.19.04
6. Notes
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7. Description control
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