Electromagnetic Tethers as Deorbit Devices-Numerical Simulation of Upper-Stage Deorbit Efficiency
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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