Electrodynamic Control for Spacecraft Attitude Stability in the Geomagnetic Field

摘要

The electrodynamic method of spacecraft attitude control is studied in an octupole geomagnetic field approximation. An analytical derivation is given for refined laws of control over spacecraft electrodynamic parameters, which ensure the required spacecraft guidance. Spacecraft equilibrium position is proved to be stable under continually acting disturbances. The effectiveness and practical feasibility of the proposed spacecraft attitude control method is confirmed by numerical analysis.