| Summary: | The objective of this thesis was to present a design proposal on a modular mechanicalstructure for a nanosatellite. The size of the structure should follow the CubeSatstandards. This standard divides satellites in units (U), where 1U is equivalent to acube where sides measure 100 mm. 2U corresponds to the same volume and size as2 assembled 1U structures, and so on. The focus was to develop a structure in theorder of 3U and 6U. At the integration in the satellite launch rocket, there are a couple of differentinterfaces, where the structure is adapted to common ones; P-POD and CSD. Toadapt the structure between both of them was part of the challenge. Most of the work consisted of concept generation and computer aided design. Aliterature study with focus on earlier work, modularity, materials and robustconstruction was also carried out. The finished structure was tested with digital toolsagainst some of the strains that satellites are exposed to, with good results. Thestructure´s modularity consists of relatively free mounting of the payload, and that thetransition between the different interfaces and sizes takes place in a smooth manner. According to the requirement specification all applicable objectives where achieved,except the weight criteria on the 3U-structure for CSD that exceeded it by 45 grams.A brief competitive analysis was carried out which showed positive results. A coupleof the recommendations for further work was to perform a proper cost analysis andthe manufacturing of a prototype for further assessments.
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