Design and management of spacecraft conducted safety margin

The purpose of the Spacecraft 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 equipments. The aim of this paper is to demonstrate the use of various Computer Aided Design (CAD) tools, ranging from PC spreadsheets, SPICE compatible circuit analysis programs to large scale simulation using TDAS EMC, in the design and management of spacecraft differential CSM. The analysis described is 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 emission payload