The Thermal Control System (TCS) utilizes a number of approaches to maintain a stable operational temperature throughout the satellite. Temperature extremes can be dealt with by active or passive means.  Active temperature control is accomplished by use of thermostatically controlled heaters or monitoring thermocouples and actively cycling hearers on and off. In addition units can be turned off and on to affect the temperature in a specific area. Passive thermal control is accomplished by use of reflective surfaces to reject absorption of heat or to radiate excess heat away, or use of non-reflective surfaces to absorb heat. In addition thermally conductive materials can be employed to evenly distribute the heat over a specific area and thermal isolating materials are used to prevent conduction of heat into an area. Some of the reflective surfaces are Quarts Mirrors applied to a surface and milar blankets secured over areas. Non-reflective surfaces can be painted with material to increase the heat absorption, an example is the use of black paint. Thermally conductive surfaces include metal to metal contact and can be the use of a thermally conductive material between the unit and mounting surface to increase conductivity. Thermal isolation is accomplished by use of a thermally non conductive material between panels or the unit and the panel.

Temperatures in different areas of the satellite can drop to less than -180 degrees C at the end of the solar panels when the satellite is in an eclipse and other areas can exceed 80 degrees C when you reach solstice seasons so thermal control does play a major roll.