Design Optimization for AM of MECSE CubeSat’s Mechanical System

• Autor(a) principal: Esteves, Miguel Costa Gonçalves
• Data de Publicação: 2018
• Tipo de documento: Dissertação
• Idioma: eng
• Título da fonte: Repositório Científico de Acesso Aberto de Portugal (Repositórios Cientìficos)
• Texto Completo: http://hdl.handle.net/10400.6/8865
• topic: Cubesat; Fabricação Aditiva; Mecse; Otimização Topológica; Domínio/Área Científica::Engenharia e Tecnologia::Engenharia Aeronáutica

Magnetohydrodynamics/Electrohydronamics CubeSat Experiment (MECSE) is an under development CubeSat at University of Beira Interior (UBI), in a collaboration effort between C-MAST (Center for Mechanical and Aerospace Science and Technologies) and CEiiA (Centre of Engineering and Product Development). MECSE’s mission is to validate the theory that an electromagnetic field can re-shape the layer of plasma allowing communication during atmosferic re-entry of vehicles, avoiding out the Radio Frequency (RF) blackout. Currently MECSE presents a classic structure composed by one top and one end plate, connected by to side frames, connected itself by six ribs. All this structural elements are made of aluminium 7075. The goal of this masters dissertation is to develop a new structure by means of topology optimization with the goal of being produced by additive manufacturing, ensuring the structural integrity of the CubeSat and all of its components in its interior, vital to the sucess of the mission. The adopted approach to reach this new stucture started by the creation of an aluminium shell structure with the dimensions of the MECSE. Mass points were applied in the Center of Gravity (CG) of which systems an attached to the structure with rigid connectors. Constraints and loads were applied according to the requirements defined by the MECSE’s launch provider as well as the topology optimization’s objectives. The optimized structures obtained were then analyzed in order to validate the optimization process and the new structure. A ligther structure was achieved, with a mass saving of 115g. Attachements for all the components inside were defined as weel as an methodology for the assembly of the CubeSat. This final optimized geometry was reanalyzed and was concluded that a new assembly methodology must be developed since the proposed fragilize the stucture by reducing its first natural frequency for less than the requirements.