Analytical time-dependent model for satellite thermal balance

This development shows the design and analysis of thermal control balance of a satellite in the GEO orbit. Keeping all subsystem of the spacecraft in the allowable range at all mission duration is the main goal of the thermal control subsystem. The purpose of the thermal design for a satellite is to keep all the elements of the satellite system within their temperature range limits for all mission phases. Also, for evaluation of satellite thermal design it is necessary to obtain the temperature distribution of all satellite components, using test or analysis. This kind of satellite is used to link satellite-earth communications, and may consist of some subsystems such as battery, computer, and communication payload. Honeycomb panel are assumed to be as satellite structure. For illustration the temperature distribution of spacecraft subsystem, it is needed to solve transient energy equation for each subsystem. Because the spacecraft subsystems are thermally coupled, a system of equations must be solved to finding the temperature distribution each subsystem [Karam, 1998].