Article ID Journal Published Year Pages File Type
10681470 Aerospace Science and Technology 2005 8 Pages PDF
Abstract
This study presents the analytical results of the dynamic behavior of an electrodynamic tether applied to a deorbit system in elliptical orbits. Parametric analyses of tether dynamics with variations in the ballast mass, the mass of the mother ship, and the tether length were performed in order to determine the range of eccentricity of the elliptical orbit in which the deorbit mission is possible. In addition, a new method for stabilizing the tether dynamics by regulating the tether current was proposed in order to expand the limit of eccentricity of the elliptical orbit in which the deorbit mission can be performed. The duration of the deorbit mission and the possibility of the tether being cut by debris during the mission were also analyzed in order to demonstrate the deorbit performance of the system.
Related Topics
Physical Sciences and Engineering Engineering Aerospace Engineering
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