Abstract
In this work, a three-axis attitude control of an isoinertial magneto-Coulombic satellite is proposed. The equation is derived for an isoinertial spacecraft, and the stability and control characteristics are developed for a set of given initial conditions. The design is based on general averaging theory which provides the tools for obtaining three-axis controllability of the isoinertial magneto-Coulombic system for any initial angular velocity of the spacecraft without accounting the periodicity of the Earth’s magnetic field. The asymptotic stabilization of the proposed system is proved for a proportional and derivative control algorithm. Finally, the effect of failure of one of the electrostatic charged shells on the attitude stabilization is considered and also, the performance between intact and failure cases is discussed as well. Simulations are carried out for various initial orientations and angular velocities to show the efficacy of the proposed isoinertial magneto-Coulombic attitude control system.
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