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. (10 pages)


    Zugriff

    Zugriff prüfen

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Design and management of spacecraft conducted safety margin

    Atkins, D.J. / Bisognin, P. | IET Digital Library Archive | 1995


    Prediction and measurement of spacecraft conducted safety margin

    Atkins, D.J. / Bisognin, P. | IET Digital Library Archive | 1997


    Prediction and measurement of spacecraft conducted safety margin

    Atkins, D.J. / Bisognin, P. | Tema Archiv | 1997