Constraint Analysis of Formation Satellites Based on Reaction Flywheel

The theoretical variation of the flywheel angular momentum is given by means of analyzing the attitude dynamics and the disturbance torque of satellite. For the satellite which use magnetorquers for momentum unloading, the change law of the angular momentum has been researched. For formation satellites which require frequent formation control, the change function of the angular momentum under the effect of short-term constant disturbance torque generated by the formation thruster is given, and the need of maximum angular momentum of flywheel under the influence of formation control is obtained. Finally, the maximum time allowed for single-pulse and multi-pulse formation control under the limited angular momentum capability is analyzed, which provides a basis for formation control strategy planning.