Abstract
The thermal control system (TCS) is an integral part of spacecraft. Its purpose is to maintain all the components of a spacecraft within their respective temperature limits. Considering orbital position and attitude of spacecraft, different sources of thermal energy acting on a spacecraft; solar radiation, Albedo, earth emitted infrared, and heat generated by onboard equipment. Therefore, the thermal control system is different for every spacecraft. In general, there are two types of TCS, passive and active. Multi-layer insulation (MLI) is considered as a passive type. MLI closely spaced layers of aluminized Mylar or Kapton alternated with a course net material. Insulation reduces the rate of heat flow per unit area between two boundary surfaces and prevents a large heat influx. SC model in Low Earth Orbit (LEO) is created by thermal desktop program, in order to launch a parametric study to check design of thermal control elements ( Radiators , Heaters , MLI ) by calculating the temperature field along the equipment panel and verify that the maximum and minimum temperature of the lower sheet of the panel is within the design range of temperature from 0 C up to 35 C .Verifying the optimum selection of the power of heaters and the correct distribution of them along the panel zones is performed..
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