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dc.contributorPérez Martínez, Marco Antonio
dc.contributor.authorBelart Bayo, Oscar
dc.contributor.otherUniversitat Politècnica de Catalunya. Departament de Resistència de Materials i Estructures a l'Enginyeria
dc.date.accessioned2012-10-30T12:28:16Z
dc.date.available2012-10-30T12:28:16Z
dc.date.issued2012-07
dc.identifier.urihttp://hdl.handle.net/2099.1/16425
dc.description.abstractAerocapture is a brand new technique of orbit insertion, which consists in the energy depletion of a spacecraft using atmospheric drag. This decelerates the space vehicle and changes its trajectory from hyperbolic orbit to elliptic orbit. Then two propulsive maneuvers must be performed in order to obtain the desired final orbit. This project seeks to assess the viability of aerocapture. It includes an implementation of a simulation tool so-called AECASIM1 that is able of simulating the aerocapture maneuver. This software contains simple environment and vehicle models that help to describe the desired aerocapture problem for its analysis. PredGuid guidance algorithm was implemented and adapted to this project’s objectives and scenario. In order to analyse the performances of this maneuver, four essential parameters were varied and some conclusions about their influence on aerocapture were drawn. Furthermore, capturable corridors were constituted with respect to the different parameter variations and were also compared between them, in order to distinguish the best possible configuration. Finally, a comparison with regular propulsive methods was performed. It revealed that with aerocapture technique great fuel savings can be achieved. For the studied case, this allows to increase the vehicle mass about a 77% and hence to rise payload mass or to reduce the initial mass approximately by a half, reducing with this the costs of the mission.
dc.language.isoeng
dc.publisherUniversitat Politècnica de Catalunya
dc.rightsAttribution-NonCommercial-NoDerivs 3.0 Spain
dc.rights.urihttp://creativecommons.org/licenses/by-nc-nd/3.0/es/
dc.subjectÀrees temàtiques de la UPC::Aeronàutica i espai::Astronàutica
dc.subjectÀrees temàtiques de la UPC::Aeronàutica i espai::Aeronaus::Coets
dc.subject.lcshSpace vehicles--Orbital assembly
dc.subject.lcshSpace flight
dc.subject.otherAerocaptura tècnica, Inserció orbital
dc.titleStudy of feasibility of a mission to Mars using aerocapture technique
dc.typeMaster thesis (pre-Bologna period)
dc.subject.lemacMart (Planeta)
dc.subject.lemacVol espacial
dc.subject.lemacVehicles espacials
dc.rights.accessOpen Access
dc.audience.educationlevelEstudis de primer/segon cicle
dc.audience.mediatorEscola Tècnica Superior d'Enginyeries Industrial i Aeronàutica de Terrassa


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Except where otherwise noted, content on this work is licensed under a Creative Commons license: Attribution-NonCommercial-NoDerivs 3.0 Spain