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

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

Description

Title: Preliminary Structural Sizing Of a Modular Microsatellite Based on System Engineering Considerations
Author/s:
  • Ravanbakhsh, Alí
  • Franchini, Sebastian Nicolas
Item Type: Presentation at Congress or Conference (Article)
Event Title: 3rd International Conference on Multidisciplinary Design Optimization and Applications
Event Dates: 21/06/2010 - 23/06/2010
Event Location: París, Francia
Title of Book: Proceedings of the 3rd International Conference on Multidisciplinary Design Optimization and Applications
Date: 2010
Subjects:
Faculty: E.U.I.T. Aeronáutica (UPM)
Department: Tecnologías Especiales Aplicadas a la Aeronáutica [hasta 2014]
Creative Commons Licenses: Recognition - No derivative works - Non commercial

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Abstract

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

More information

Item ID: 7512
DC Identifier: http://oa.upm.es/7512/
OAI Identifier: oai:oa.upm.es:7512
Official URL: http://www.asmdo.com/conference2010/
Deposited by: Memoria Investigacion
Deposited on: 16 Jun 2011 07:34
Last Modified: 20 Apr 2016 16:38
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