Prediction and measurement of spacecraft conducted safety margin

The purpose of the spacecraft conducted safety margin (CSM) is to ensure that the frequency and time domain conducted emissions on the primary power supply are at least a factor of 2 (6dB) less than the conducted susceptibility test levels imposed on electrical equipment. This paper explains the purpose of the CSM and the means by which it is predicted in the narrow band frequency domain, using various CAD tools, and verified by measurements at module and spacecraft level. The analysis and measurements described are based on the work carried out by Matra Marconi Space under ESA contract No 8874/91/NL/PR to confirm the conducted electromagnetic compatibility of the European Polar Platform with the ENVISAT-1 mission payload