Design and development of thermal test model of a microsatellite for thermal balance test

Purpose This paper seeks to provide an insight into the design and development of the thermal test model TTM of XSat, a 120kg class microsatellite, being developed at the Centre. This model was specifically constructed for carrying out a thermal balance test TBT in a 4m diameter vertical thermal vacuum chamber. Designmethodologyapproach The construction of the thermal model followed a structural mockup model which was modified thermally to suit the purpose. Specific and careful consideration was given to the geometry and, more importantly, thermal characteristics such as thermal mass, surface properties, etc. to mimic the actual satellite configuration as closely as possible. Test plans were devised to qualify the fabricated components to meet the outgassing and other thermal requirements for the model. Design and qualification of supporting frame and linkages for TBT are also covered. Findings It is possible to simulate the thermal characteristics of a microsatellite in orbit under a different mission scenario through proper scaling and using alternative material options while developing TTM. Originalityvalue The paper discusses in detail the simplified costeffective approach of constructing TTM and also outlines the various issues to be considered for a TBT. It provides valuable information needed for microsatellite designers.