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dc.contributorMasdemont Soler, Josep
dc.contributor.authorHerrera Sucarrat, Elisabet
dc.contributor.otherUniversitat Politècnica de Catalunya. Departament de Matemàtica Aplicada I
dc.date.accessioned2009-03-09T17:22:42Z
dc.date.available2009-03-09T17:22:42Z
dc.date.issued2008-10
dc.identifier.urihttp://hdl.handle.net/2099.1/6546
dc.description.abstractA geosynchronous Transfer Orbit (GTO) is a type of transfer around the Earth between a low Earth orbit (LEO) and the geostationary orbit (GEO). After the launch to a LEO orbit, the orbit of spacecraft has the same inclination with respect to the equator, than the latitude of the launch site on the Earth where the spacecraft was launched. In order to transfer to a GEO orbit the inclination must be reduced to zero. During a GTO it may happen that because of many different problems, the spacecraft may not arrive to a GEO orbit and instead, it may remain in an inclined high elliptical orbit. The aim of this project is to compare in terms of _v, different ways of transfers between these elliptical orbits and the geostationary orbit. This masters thesis presents a brief study of different ways of transfer between an elliptical orbit and the geostationary orbit, using the restricted three body problem (RTBP) as the mathematical model. In this situation, a spacecraft moves under the gravitational forces of two massive bodies, which at the same time describe circular orbits around their common center of mass. The RTBP has 5 equilibrium points which have been studied in deep in the past. The results contained in this project are related with the equilibrium point L1, which is the one that lies between the two massive bodies.
dc.language.isoeng
dc.publisherUniversitat Politècnica de Catalunya
dc.rightsAttribution-NonCommercial 3.0 Spain
dc.rights.urihttp://creativecommons.org/licenses/by-nc/3.0/es/
dc.subjectÀrees temàtiques de la UPC::Física::Astronomia i astrofísica::Cosmologia i cosmogonia
dc.subject.lcshThree-body problem.
dc.subject.lcshCelestial mechanics
dc.subject.otherrestricted three body problem
dc.subject.otherLEO orbit
dc.subject.otherGEO orbit
dc.titleStudy of LEO to GEO transfers via the L1 Sun-Earth or Earth-Moon libration points
dc.typeMaster thesis (pre-Bologna period)
dc.subject.lemacProblema dels tres cossos
dc.subject.lemacMecànica celest
dc.subject.amsClassificació AMS::70 Mechanics of particles and systems::70F Dynamics of a system of particles, including celestial mechanics
dc.rights.accessOpen Access
dc.audience.educationlevelMàster
dc.audience.mediatorUniversitat Politècnica de Catalunya. Facultat de Matemàtiques i Estadística


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