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 equipment. 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 mission payload. (10 pages)
Design and management of spacecraft conducted safety margin
1995-01-01
1 pages
Article (Journal)
English
time domain conducted emissions , aerospace computing , spacecraft differential CSM , Matra Marconi Space , spreadsheet programs , primary power supply , electrical equipment , TDAS EMC , conducted electromagnetic compatibility , spacecraft conducted safety margin , large scale simulation , ENVISAT-1 mission payload , SPICE compatible circuit analysis programs , artificial satellites , design , European Polar Platform , frequency domain conducted emissions , electromagnetic compatibility , safety , ESA , conducted susceptibility test levels , electromagnetic interference , SPICE , circuit analysis computing , CAD , digital simulation , management , CAD tools , PC spreadsheets
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