The paper deals with a satellite in a circular near-Earth orbit, perturbed due to J2 Earth's oblateness. The satellite interacts with the geomagnetic field by the moments of Lorentz and magnetic forces. The octupole approximation of the Earth's magnetic field is used. The possibility of electrodynamical attitude control for the satellite's stabilization in the orbital frame is analyzed. Once the problem of electrodynamical compensation of disturbing torque is solved, we can obtain the control algorithms for the satellite electromagnetic parameters which allows to stabilize the satellite attitude position in the orbital frame in the presence of disturbing gravity gradient torque. The total stability of the satellite programmed motion is proved analytically and verified by computer modeling.

Original languageEnglish
Pages (from-to)219-227
Number of pages9
JournalActa Astronautica
Volume141
DOIs
StatePublished - 1 Dec 2017

    Scopus subject areas

  • Aerospace Engineering

    Research areas

  • Attitude stabilization, Electrodynamic attitude control system, Geomagnetic field, Perturbed orbit, Satellite

ID: 18083423