Preliminary Structural Sizing Of a Modular Microsatellite Based on System Engineering Considerations

Ravanbakhsh, Alí y Franchini, Sebastian Nicolas (2010). Preliminary Structural Sizing Of a Modular Microsatellite Based on System Engineering Considerations. En: "3rd International Conference on Multidisciplinary Design Optimization and Applications", 21/06/2010 - 23/06/2010, París, Francia.

Descripción

Título: Preliminary Structural Sizing Of a Modular Microsatellite Based on System Engineering Considerations
Autor/es:
  • Ravanbakhsh, Alí
  • Franchini, Sebastian Nicolas
Tipo de Documento: Ponencia en Congreso o Jornada (Artículo)
Título del Evento: 3rd International Conference on Multidisciplinary Design Optimization and Applications
Fechas del Evento: 21/06/2010 - 23/06/2010
Lugar del Evento: París, Francia
Título del Libro: Proceedings of the 3rd International Conference on Multidisciplinary Design Optimization and Applications
Fecha: 2010
Materias:
Escuela: E.U.I.T. Aeronáutica (UPM) [antigua denominación]
Departamento: Tecnologías Especiales Aplicadas a la Aeronáutica [hasta 2014]
Licencias Creative Commons: Reconocimiento - Sin obra derivada - No comercial

Texto completo

[img]
Vista Previa
PDF (Document Portable Format) - Se necesita un visor de ficheros PDF, como GSview, Xpdf o Adobe Acrobat Reader
Descargar (96kB) | Vista Previa

Resumen

In this paper a system engineering approach toward the preliminary design of the structure subsystem of a microsatellite has been introduced. This work is on the context of the UPMSat-2 UNION, a university class small satellite under design at Universidad Politécnica de Madrid (Spain), whose aim is to introduce a reliable platform for different types of missions and payloads. Launch loads are pre assumed based on the data provided by Ariane Structure for Auxiliary Payload 5, ASAP5 launcher with the condition of launching the satellite as a secondary payload. The satellite main configuration includes four trays. One tray is assumed for mission payload and the three others for accommodating the instruments related to the other subsystems. The structure subsystem mass is calculated from the analytical formulas in order to fulfil the static constraints and frequency requirement. The main purpose of the work is finding out in a simple way the primary structure behaviour before entering the FEM and more detailed analysis. From system engineering approach it is desirable if the satellite platform can offer as much as volume and mass for the payload, because it results to providing more diversity for payload types. Based on this, different satellite configurations adjustable to the envelope of piggyback launch are considered and their provided payload volume in comparison with the structural mass required to stand the static loads and fulfil frequency requirements is investigated

Más información

ID de Registro: 7512
Identificador DC: http://oa.upm.es/7512/
Identificador OAI: oai:oa.upm.es:7512
URL Oficial: http://www.asmdo.com/conference2010/
Depositado por: Memoria Investigacion
Depositado el: 16 Jun 2011 07:34
Ultima Modificación: 20 Abr 2016 16:38
  • Open Access
  • Open Access
  • Sherpa-Romeo
    Compruebe si la revista anglosajona en la que ha publicado un artículo permite también su publicación en abierto.
  • Dulcinea
    Compruebe si la revista española en la que ha publicado un artículo permite también su publicación en abierto.
  • Recolecta
  • e-ciencia
  • Observatorio I+D+i UPM
  • OpenCourseWare UPM