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Dynamic design of a cube-shaped satellite excited by launch vibrations

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Dynamic design of a cube-shaped satellite excited by launch vibrations

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dc.contributor.advisor Rovira Cardete, Andrés es_ES
dc.contributor.author Fraile Izquierdo, Sergio es_ES
dc.contributor.author Pila Vigalondo, Alejandro
dc.date.accessioned 2015-05-26T08:16:43Z
dc.date.available 2015-05-26T08:16:43Z
dc.date.created 2014-12-19
dc.date.issued 2015-05-26
dc.identifier.uri http://hdl.handle.net/10251/50741
dc.description.abstract The objective of this Final Project is the structural design of a small cube–shaped satellite. Its primary structure should endure all launching vibrations. To fulfil that objective, a 3D Model of the satellite and a dynamic analysis must be done. The satellite has been designed as a multipurpose platform, so it can satisfy all possible client requirements in order to put different payloads into orbit. To begin with, a general satellite with an arbitrary payload has been designed with the future intention to adapt the current design to each client if necessary. To address the problem the following procedure has been used. First, and with a multi–platform CAD/CAM/CAE commercial software suite called CATIA (Computer Aided Three–Dimensional Interactive Application) a Computer Aided Design Model must be designed. Later, once the parameterized model is created, the engineering simulation software (CAE) ANSYS will be used to study the structural behaviour of the satellite during launch. The scope of this project is to design a multipurpose satellite bus that satisfies the conditions of the ASAP Document (see Section 6.1). That is, a satellite which can withstand all inertial forces and loads during launch in the 0–100 Hz spectrum, with a correctly aligned center of gravity, small enough moments of inertia, and with its natural frequencies above a certain value for each axis. The bus must fulfil the specifications given by the corresponding launch vehicle1 manufacturer, so to choose the launch vehicle, a comparative study has been made between the different options evaluating reliability, availability of the information offered and payload requirements. Once this study has been carried out, the most restrictive launcher has been selected. This has been done in order to be able to use a wider range of LV. es_ES
dc.format.extent 140 es_ES
dc.language Inglés es_ES
dc.publisher Universitat Politècnica de València es_ES
dc.rights Reserva de todos los derechos es_ES
dc.subject FEM Model es_ES
dc.subject Ariane-5 es_ES
dc.subject ANSYS es_ES
dc.subject CATIA (Computer Aided Three–Dimensional Interactive Application) es_ES
dc.subject Microsatellite es_ES
dc.subject.classification INGENIERIA MECANICA es_ES
dc.subject.other Ingeniería Aeronáutica - Enginyeria Aeronàutica
dc.title Dynamic design of a cube-shaped satellite excited by launch vibrations es_ES
dc.type Proyecto/Trabajo fin de carrera/grado es_ES
dc.rights.accessRights Abierto es_ES
dc.contributor.affiliation Universitat Politècnica de València. Escuela Técnica Superior de Ingeniería del Diseño - Escola Tècnica Superior d'Enginyeria del Disseny es_ES
dc.description.bibliographicCitation Fraile Izquierdo, S.; Pila Vigalondo, A. (2014). Dynamic design of a cube-shaped satellite excited by launch vibrations. Universitat Politècnica de València. http://hdl.handle.net/10251/50741 es_ES
dc.description.accrualMethod Archivo delegado es_ES


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