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This document describes research into developing electrically conductive thermal control coatings for use on spacecraft. Specifically, it discusses formulations using sodium silicate binders with fired zinc oxide and aluminum oxide pigments. The coatings were required to have low electrical resistivity (less than 1x105 ohm-m2), an absorptance around 0.55, and an emittance of 0.90, while maintaining these properties after 2 years of exposure to solar wind conditions. Initial efforts using metals were unsucce

Author

hossein

Language

EN