One of the main problems in Space Technology is the heat flow. Therefore the Thermal Control Group is developing ways to shield the CubeSat against the high temperature fluctuation in space without the usage of heat conduction or convection. A widespread method for this kind of problem are Multi-Layer-Insulations and Second-Surface-Mirrors. In addition to the heat radiation is the exhaust heat of the electrical parts. Our aim is to use well-conducting materials which will transport the heat from the inside to the Second-Surface-Mirrors and then radiate it into Space. For more sensitive parts, e.g. batteries, it is necessary to heat them up when there is no active sun radiation on the CubeSat. This Problem could be solved with heating wire or a clever circulation of the exhaust heat from the OBC.

As a supportive measure for the design, we use simulation tools. One of these tools is SPENVIS, which is developed by the ESA and is capable of calculating the radiation for an element set of one trajectory. With this data it is possible to estimate the degree of degeneration of our parts. Furthermore we use FEMM as a finite element method for calculating the heat gradient inside the CubeSat.