Abstract
Satellites, normally, are subject to large variations in temperature due to its orbit. On the other hand, the equipment that make up feature limits (minimum and maximum) of temperature must not be exceeded so that the satellite's operation is not compromised. In this way, this paper presents a numerical comparison between a plane radiator and finned radiator in critical operating conditions. Designed to operate in passive thermal control of satellites, these devices reject the heat generated by electronic components and minimize the absorption of heat from external sources (especially the sun) in order to maintain the temperature of the satellite components within their operating ranges. For this purpose, two algorithms in Fortran® were developed for solving the nonlinear system of equations which govern the conductive-radioactive coupling in both radiators. These equations were discretized by two-dimensional Finite Volume Method and the resulting system was solved with the application of Tri-Diagonal Matrix Algorithm combined with an iterative process. The numerical obtained results show the temperature profiles to both radiators studied in critical operation conditions.
Published Version
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