Advanced numerical study of the three-axis magnetic attitude control and determination with uncertainties

Attitude motion of a satellite equipped with magnetic control system is considered. System comprises of three magnetorquers and one three-axis magnetometer. Satellite is stabilized in orbital reference frame using PD controller and extended Kalman filter. Three-axis attitude is analyzed numerically with advanced assumptions: inertia tensor uncertainty, disturbances of unknown nature, magnetometer errors are taken into account. Stabilization and determination accuracy dependence on orbit inclination is studied. •Three axis attitude utilizing magnetorquers and magnetometer is considered.•Stabilization is provided with PD-controller and Kalman filter.•Disturbances, inertia tensor and magnetometer errors are taken into account.•Stabilization accuracy dependence on orbit inclination is provided.