Abstract
One of the biggest challenges in space systems engineering is simulating the space environment when developing and testing various components, subsystems and entire satellites prior to a mission. Therefore, a space simulation system is needed to reproduce the vacuum of space, the intense solar radiation and the extreme temperature variations. Such a facility can be extremely complex and expensive. One way to reduce costs is working with small-sized systems and implementing a compact facility capable of fulfilling multiple applications. The system must be useable as a space simulator, a thermal-vacuum chamber or a standard vacuum chamber, all the while allowing a quick and easy transition between operational modes. This requires the implementation of a removable thermal shroud capable of reaching −150 °C and +150 °C. First, the thermal shroud geometry is defined and the nitrogen flow and temperature requirements are calculated. The second step is a steady-state heat transfer and structural analysis, performed using the software Ansys in order to obtain the temperature, stress and deformation. The last step is the virtual integration of the thermal shroud and vacuum chamber using the software Catia V5.
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