Attitude motion of the axisymmetrical gyrostat-satellite affected by active magnetic control

A magnetic attitude control system, owing to absence of moving parts and certain simplicity of realization, is common used in practice. Such kind of systems require low power, are relatively lightweight and inexpensive. Due to these features the active magnetic attitude control system is one of the most common attitude control system implemented on board of small satellites. The serious limitation during their realization is a control torque vector direction singularity. Control systems with magnetic actuators combined with other active or passive control elements, for example with a gravitational boom and/or with flywheels, are more effective and more often are realized in practice. In the present work a dynamically symmetrical satellite equipped by a pitch flywheel and active magnetic control system is considered. The general approaches of magnetic control algorithm design are considered. Realization of the proposed method is illustrated by some special cases.