Electrodynamic attitude stabilization of a satellite in an indirect position

The problem of triaxial stabilization of the satellite position in the orbital reference frame is considered. The satellite moves in a medium-height circular orbit, has a controlled electrostatic charge and its own magnetic moment. The question is raised on the possibility of implementing such a system of electrodynamic control of the angular position of the satellite in which the influence of the disturbing gravitational torque is compensated by additional terms in the control torques. A constructive analytical approach to the analysis of nonlinear stability in the problem of the triaxial attitude stabilization of the satellite is presented. The constructed mathematical model has no restrictions on the orbit inclination, on the accuracy of the model of the Earth’s magnetic field as well. The theorem on the asymptotic stability of the stabilized angular position of the satellite is proved. The theorem substantiates the possibility of building the specified control system. Nonlinear analysis is based on the direct Lyapunov method. The effectiveness of the developed attitude control system has been confirmed by computer modeling.