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dc.rights.licenseopenen_US
hal.structure.identifierLaboratoire de l'intégration, du matériau au système [IMS]
dc.contributor.authorSALOTTI, Jean-Marc
dc.date.accessioned2022-07-12T12:36:46Z
dc.date.available2022-07-12T12:36:46Z
dc.date.issued2022-02
dc.identifier.issn0094-5765en_US
dc.identifier.urihttps://oskar-bordeaux.fr/handle/20.500.12278/140438
dc.description.abstractEnSeveral proposals exist for human Mars mission architectures. An important question to resolve is to determine the most appropriate size of the launcher to minimize the costs, without compromising with risks, efficiency and future developments. Strategic choices are proposed. A fundamental choice is the direct to surface option, one that greatly simplifies the architecture of the mission and avoids a complex and costly LEO assembly of a giant vehicle. The second is aerocapture for Mars orbit insertion. The third is the choice of the EDL systems with highest TRL in order to minimize the risks of the mission and at the same time to avoid possible cost overruns due to qualification issues. Minimization is achieved for a crew of three. It is shown that an LEO capacity of the order of 100 to 110 tonnes is sufficient to carry out a Mars mission using 5 heavy launchers. This result is of particular interest for the countries currently developing super heavy launchers with such capacity, like the Starship and SLS in the USA, Long March 9 in China and similar developments in Russia. If Europe were also interested in the design of a super heavy launcher, it is shown here that it could be based on Vulcain or Prometheus engines. As the mission is rather simple and optimized with high TRL, the mission could be affordable. A roadmap is also suggested with appropriate preparatory missions for a human Mars exploration program.
dc.language.isoENen_US
dc.rightsAttribution 3.0 United States*
dc.rights.urihttp://creativecommons.org/licenses/by/3.0/us/*
dc.subject.enHuman mission to Mars
dc.subject.ensuper heavy launcher
dc.subject.enMars direct EDL: Earth
dc.subject.enAriane Super Heavy
dc.title.enLauncher size optimization for a crewed Mars mission
dc.typeArticle de revueen_US
dc.identifier.doi10.1016/j.actaastro.2021.11.016en_US
dc.subject.halSciences de l'ingénieur [physics]/Automatique / Robotiqueen_US
dc.subject.halSciences de l'ingénieur [physics]/Autreen_US
bordeaux.journalActa Astronauticaen_US
bordeaux.page235-244en_US
bordeaux.volume191en_US
bordeaux.hal.laboratoriesLaboratoire d’Intégration du Matériau au Système (IMS) - UMR 5218en_US
bordeaux.institutionUniversité de Bordeauxen_US
bordeaux.institutionBordeaux INPen_US
bordeaux.institutionCNRSen_US
bordeaux.peerReviewedouien_US
bordeaux.inpressnonen_US
bordeaux.import.sourcehal
hal.identifierhal-03438183
hal.version1
hal.exportfalse
workflow.import.sourcehal
dc.rights.ccPas de Licence CCen_US
bordeaux.COinSctx_ver=Z39.88-2004&rft_val_fmt=info:ofi/fmt:kev:mtx:journal&rft.jtitle=Acta%20Astronautica&rft.date=2022-02&rft.volume=191&rft.spage=235-244&rft.epage=235-244&rft.eissn=0094-5765&rft.issn=0094-5765&rft.au=SALOTTI,%20Jean-Marc&rft.genre=article


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