双体卫星对日定向姿态机动控制

The sun-pointing attitude maneuver control of a two-body satellite with an architecture of disturbance free payload (DFP) is investigated. According to the work mechanism of the DFP, the attitude model of the DFP is established and the relative motion between the magnet steels and the coils of maglev actuators is derived. The sun-pointing attitude maneuver strategy for the payload and the attitude tracking strategy for the platform based on PD control are proposed. The relative position control algorithm is presented to avoid collision. To improve the platform dynamic performance, the backstepping control algorithm is presented to compensate for the dynamic characteristic of the flywheels. To improve the cooperativity between the platform and the payload, the variable gain PD controller when considering relative attitude between the payload and the platform is proposed for the payload attitude maneuver.