Space solar cell edge, interconnect, and coverglass designs and their effect on spacecraft charging and plasma interactions

Abstract

One of the principal design drivers for space solar arrays is solar cell arcing into the plasma due to spacecraft charging. The amount of spacecraft charging and the resulting differential voltages on space solar cell edges and interconnects is related to the cell edge, interconnect and coverglass designs. For example, the International Space Station (ISS) did not charge up to expected levels because of its closely spaced solar cells, wrap-through interconnects, and coverglass overhangs, which serve to choke off electron collection and prevent the concomitant negative charging that would otherwise occur on its high voltage solar arrays.