Electrodynamic deorbiting of LEO satellites

In this paper we present realistic calculations of deorbiting times for a L EO satellite through the use of electrodynamic tethers. We refer to two pos sible tether systems (a bare and a conducting insulated tether) both equipp ed with an inflatable conducting balloon at the upper end. The calculations take into account average ionospheric properties and the electrical intera ction of the wire with the ionosphere. Furthermore, they have been done for several inclination orbits and include also the deviation of the tether fr om the vertical direction under the combined action of the gravity gradient and the electrodynamic forces. The results obtained for the decay times, f or typical constellation satellite, indicate that such tether systems are d efinitely of interest for the deorbiting application.