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Research Article Open Access
This paper examines the deorbit efficiency of an electromagnetic tether deorbit device when used to deorbit an upper stage at end of mission from low Earth orbit. This is done via a numerical simulation in Matlab R2013a, using ode45, taking into account perturbations the upper stage’s trajectory. The perturbations considered atmospheric drag, 3rd body (Sun and Moon), and Earth’s gravitational potential expanded into spherical harmonics.
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Author(s): Alexandru Ionel
Electromagnetic tether, orbital debris, deorbit devices, ode45, spherical harmonics, 3rd body perturbation., Electronic Materials,Optical Communication,Semiconductor Technology,Electrical Machines,Electromagnetic Transients Programs (EMTP).