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Investigation of conductive thermal control coatings by a contactless method in vacuoA technique for determining the conductance per unit area of thermal control coatings for electrostatically clean spacecraft is described. In order to simulate orbital conditions more closely, current-density-voltage (j-V) curves are obtained by a contactless method in which the paint on an aluminum substrate is the anode of a vacuum diode configuration with a tungsten filament cathode. Conductances per unit area which satisfy the International Sun Earth Explorer (ISEE) requirement were observed on black paints containing carbon and in white and green paints filled with zinc oxide which were fired in order to induce defect conductivity. Because of surface effects and the nonhomogeneous nature of paints, large discrepancies were found between measurements with the contactless method and measurements employing metallic contacts, particularly at low current densities. Therefore, measurements with metallic contacts are considered to be of questionable value in deciding the suitability of coatings for electrostatic charge control.
Document ID
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Viehmann, W.
(NASA Goddard Space Flight Center Greenbelt, MD, United States)
Shai, C. M.
(NASA Goddard Space Flight Center Greenbelt, MD, United States)
Sanford, E. L.
(NASA Goddard Space Flight Center Greenbelt, MD, United States)
Date Acquired
August 9, 2013
Publication Date
February 24, 1977
Publication Information
Publication: Proc. of the Spacecraft Charging Technol. Conf.
Subject Category
Nonmetallic Materials
Accession Number
Distribution Limits
Work of the US Gov. Public Use Permitted.
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