Abstract

Great attention is paid to long-duration spacecraft, and operational problems are often linked with their resistance to electromagnetic radiation. The range of wavelengths of 1 cm – 100 m is essential. There are many different sources of electromagnetic radiation in space but it is estimated that many of software errors can be attributed to electromagnetic impulses (EMI) generated by electrostatic discharge events (ESD) [1-4]. Note that such electromagnetic disturbances could be generated also during hypervelocity impacts. There are two different mechanisms for EMI in this case: the charge separation in expanding plasma and the electrostatic discharge initiated by local puncture of isolation and generation of a conducting medium. We discuss the theoretical considerations of beginning a multistage break down process. The equations of dynamics of the surface charge, the current in the plasma channel and the induction electrical field are developed and numerically calculated. The results are also can be applied to spontaneous breakdowns. Interest from the space industry would be decisive for resolving this problem.

Keywords: Active filters, aerospace accidents, aerospace electronics, aerospace safety, circuit faults, circuit topology, clamps, electric breakdown, electric resistance, electrostatic discharge