The magnitude of common mode voltage transients generated during the fuse blowing event following a short circuit to spacecraft structure are dependent on the electrical impedance of the current return path. The aluminium skinned panels of a conventional spacecraft structure design normally provide a low impedance fault current return path. This paper considers the implications of such events for a spacecraft whose structure includes assemblies of carbon fibre reinforced plastic (CFRP) skinned panels and ground reference rails. Results of fuse blowing tests and electrical impedance measurements on a representative spacecraft structure are used to confirm both a practical and theoretical understanding of the various coupling mechanisms involved. Simplified analysis methods are adapted for a typical CFRP structured spacecraft configuration to assess impacts of fuse blowing events on both spacecraft design and operation.
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