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Orbital debris poses significant risks to space activities and is a
threat extending into the foreseeable future. While identification
and tracking of orbital threats is actively pursued in general, we
focus on deorbiting very small satellites of the nanosat or cubesat
size with miniature tether systems. Ch.2 describes the basic
principles of electric tether physics, and outlines the geophysical
environment of LEOs where tethered nanosat flying occurs. Ch.3
develops an equivalent circuit model of an electrodynamic (ED)
tether system, and illustrates the surge currents and overvoltages
under various operating modes. Ch. 4-6 discuss the nonlinear
characteristics of electrostatic (ES), ED, and more promising
hybrid ES-ED tether dynamics, and the application of tethered
systems. Ch.7 summarizes the work, with some related discussions.
The work was initiated at Chinese Academy of Sciences (CAS,
1995-1997; 2001-2003), and is funded by Visiting Fellowship in
Canadian Government Laboratories Program (2009-2012), Natural
Sciences and Engineering Research Council (NSERC), Canada. We thank
Dr. Alfred Ng, Manager (Control and Analysis), Canadian Space
Agency (CSA), for support and advice.
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