Characterization of the EMC Performances of the CAN Bus in a Typical System Bus Architecture for Small Satellites

The cost reduction is a key factor in the preparation of new scientific missions for space exploration and therefore in the design of space craft (S/C). In order to achieve this goal, investigations are carried out in order to verify the usability of components off the shelf (COTS) and technologies widely used in the industry. In this frame, a test campaign has been performed at the European Space and Technology Centre (ESTEC) of the European Space Agency (ESA). The campaign aims at characterizing the CAN bus in terms of EMC, specifically radiated emission, in a typical configuration for a small satellite, evaluating the effect of different configurations in its performances. The CAN bus has been selected because it is considered a good alternative to the reliable MIL-STD-1553B bus, often used as control bus of a space craft