Spin-stabilized satellite magnetic attitude control scheme without initial detumbling

The angular motion of an axisymmetrical satellite equipped with an active magnetic attitude control system is considered. The dynamics of the satellite are analytically studied on the whole control loop. The control loop is as follows: preliminary reorientation along with nutation damping, spinning about the axis of symmetry, then precise reorientation of the axis of symmetry in inertial space. Reorientation starts right after separation from the launch vehicle. Active magnetic attitude control system time‐response with respect to its parameters is analyzed. It is proven that low‐inclined orbit forces low control system time‐response. Comparison with the common control scheme shows the time‐response gain. Numerical analysis of the disturbances effect is carried out and good pointing accuracy is proved.