  The magnetic plasma deorbit method has been proposed for micro and
nanosatellites in the low earth orbit (LEO). The magnetic plasma deorbit
utilizes the plasma drag force generated by the interaction between space
plasma and the magnetic field surrounding magnetic torquers (MTQs). In this
study, the plasma drag force generated by the magnetic plasma deorbit method is
estimated by using a plasma flow simulation based on the fully kinetic model.
The dependences of the plasma drag force on the MTQ angle, atmospheric plasma
density, and MTQ magnetic moment are investigated. The simulation results show
that the structures of the bow shock and magnetosphere are formed in the
vicinity of the MTQs. The predicted plasma drag force is 105.2 nN for an MTQ of
10 A m$^2$ when the MTQ magnetic moment is parallel to the satellite velocity
direction. The plasma drag force shows a strong dependence on the magnetic
moment angle. In addition, the plasma drag force is proportional to the
atmospheric plasma density and the MTQ magnetic moment. Steady drag force
generation in the magnetic plasma deorbit is validated, and the sensitivities
of the drag force to the relevant parameters are elucidated.
