| Περίληψη: | Two of the most fundamental issues that have preoccupied humanity for many centuries and will continue to concern it, given the continuation of technological development, are both the creation and the end of the universe. In recent years, science has turned to the design of CubeSats, which beyond meeting daily needs, are also the cornerstone for the subsequent construction of new satellites, that will have the potential, at some later stage of the human history, to give a final answer to the aforementioned issues. The current thesis deals with the design of a 6U-XL CubeSat using laminated composite materials, which is planned to transport a deployable robotic arm in space. At a first stage, the appropriate literature overview is made, with a special reference to material science and especially to composites, which constitute both the present and the future of aerospace applications. Followingly, the primary structural components of the CubeSat, which were designed in CATIA environment, are presented and sufficiently commented. Then all the necessary analyses (modal, quasi-static, buckling and random vibrations), which confirm at least computationally the proper functionality of the satellite during the launch, are carried out in the MSC PATRAN/NASTRAN software. Finally, an attempt is made to optimize the present structure through the study of different composite materials with the aim of reducing the total weight of the satellite, which represents one of the most crucial driving-factors of every space mission.
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