A Thermal Control System (TCS) is a subsystem that is responsible for the maintenance of temperature constraints of all the hardware components of the Cubesat. TCS is dependent of all the subsystems (including itself) as they all contribute to the overall heat equilibrium of the satellite. Most of the equipment on the spacecraft is usually designed to operate on or near room temperature (RT). The main task of the TCS is therefore to provide requisite temperatures for Cubesat components in space environment. As the conditions in space are harsh and the temperature fluctuations significant, special means have to be utilized in order to assure a properly working Cubesat.

There are two possibilities to control and stabilize the temperature on a spacecraft:

• Active temperature control. The temperature is stabilized using electrical heat exchangers
• Passive temperature control. Reflective surfaces, heat conductive materials, different paints and radiators are used to create necessary thermal condition without any use of active electric systems