An experimental investigation is conducted to understand the I-V characteristics and floating potential of a surface covered by varying amounts of dust in a plasma environment similar to that at the lunar terminator. I-V curves are measured to determine dust coverage effects on surface charging, and a non-contacting electrostatic voltmeter is used to measure dust surface charging. Results show that as dust coverage increases, the electric field created between the dust surface layer and conducting surface layer increases the possibility of arcing and breakdown.
K. Chou et al., "Experimental Investigations of Dusty Spacecraft Charging at the Lunar Terminator," Proceedings of the AIAA SPACE 2015 Conference and Exposition (2015, Pasadena, CA), American Institute of Aeronautics and Astronautics (AIAA), Sep 2015.
The definitive version is available at https://doi.org/10.2514/6.2015-4560
AIAA SPACE 2015 Conference and Exposition (2015: Aug. 31-Sep. 2, Pasadena, CA)
Mechanical and Aerospace Engineering
Keywords and Phrases
Dust; Electric fields; Plasma devices; Plasma flow; Plasma jets; Spacecraft; Surface charge; Voltmeters; Conducting surfaces; Electrostatic voltmeter; Numerical investigations; Particle-in-cell code; Plasma parameter; Spacecraft charging; Surface charging; University of Southern California; Plasma diagnostics
International Standard Book Number (ISBN)
Article - Conference proceedings
© 2015 American Institute of Aeronautics and Astronautics (AIAA), All rights reserved.
01 Sep 2015