Design and management of spacecraft conducted safety margin

Author

Atkins, D.J. ; Bisognin, P.

Author_Institution

Matra Marconi Space, Bristol, UK

fYear

1995

fDate

34831

Firstpage

42461

Lastpage

410

Abstract

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

Keywords

CAD; SPICE; aerospace computing; artificial satellites; circuit analysis computing; digital simulation; electromagnetic compatibility; electromagnetic interference; safety; spreadsheet programs; CAD tools; ENVISAT-1 mission payload; ESA; European Polar Platform; Matra Marconi Space; PC spreadsheets; SPICE compatible circuit analysis programs; TDAS EMC; conducted electromagnetic compatibility; conducted susceptibility test levels; design; electrical equipment; frequency domain conducted emissions; large scale simulation; management; primary power supply; spacecraft conducted safety margin; spacecraft differential CSM; time domain conducted emissions;

fLanguage

English

Publisher

iet

Conference_Titel

Design Tools for EMC, IEE Colloquium on

Conference_Location

London

Type

conf

DOI

10.1049/ic:19950659

Filename

473135