Design of MECSE Nanosatellite Mechanical Subsystem

• Autor(a) principal: Azevedo, Ana Rita Moreira
• Data de Publicação: 2017
• Tipo de documento: Dissertação
• Idioma: eng
• Título da fonte: Repositório Científico de Acesso Aberto de Portugal (Repositórios Cientìficos)
• Texto Completo: http://hdl.handle.net/10400.6/7952
• topic: Análises de Elementos Finitos Em Cubesats; Cubesat; Impacto Térmico.; Magnetohydrodynamics/Electrohydrodynamics Cubesat Experiment; Mecse; Nanosatélite; Subsistema Mecânico do Mecse; Domínio/Área Científica::Engenharia e Tecnologia::Engenharia Aeronáutica

Magnetohydrodynamics/Electrohydrodynamics CubeSat Experiment (MECSE) is the first Cube- Sat being developed at the University of Beira Interior (UBI) and it is an under development Nanosatellite resulting from the collaboration between C-MAST (Center for Mechanical and Aerospace Science and Technologies) and CEiiA (Centre of Engineering and Product Development). MECSE’s mission is to create a benchmark for the future validation of the theory that an Electromagnetic field can re-shape the layer of plasma surrounding a spacecraft, and therefore allow communications during the so-called atmospheric re-entry Radio Frequency (RF) blackout phase. When it comes to scientific space research there is a need to create a bridge between the scientific goals and the engineering feasibility. In order for the mission to take shape, the development of the product CubeSat shall meet scientific requirements as well as production limitations and space regulations. This master dissertation aims to preliminarily develop MECSE’s Mechanical Subsystem. In this work, a Mechanical Subsystem configuration that ensures the structural reliability during launch, as well as on orbit was developed. The approach adopted for the design of MECSE’s Mechanical System was to, first, define the different project requirements, and then, COTS hardware components were selected based on similar previous missions and their requirements were specified. The project also presents Design Requirements that were specified based on the CubeSat Design Specifications, and the launch platform P-POD. Finally, the materials for the primary structure of the CubeSat had to be selected. A trade-off was performed comparing several material properties (e.g. thermal conductivity, electrical conductivity, workability and others) and the aluminum alloy 7075 T6 was chosen. The spacecraft must sustain a set of mechanical loads without permanent deformation, with a certain margin of safety to prevent the uncertainties in the loading values during launch. A finite element analysis validated the capacity of MECSE to sustain the linear static loads and static temperature during launch and on-orbit.The components were evaluated and, with exception of the Side Frames, the primary structural components should have their thickness reduced, since they presented high margins of safety to stress and strain. The thermal impact study showed that the subsystems will have their envelope of operations conditioned by the angle between the orbit plane and the solar vector. In order to increase the envelop of operations it was recommended the use of aerogel.