Modeling And Control Of The Satellite With Dual Axis Solar Array Actuator

This dissertation investigates a kind of satellite consisting of a central rigid body and two symmetric solar arrays, adopting the dual axis solar array drive mechanism. Then the modeling, attitude control, vibration suppression and simulation of flexible satellite are well investigated on the basis of that. The main research is given as follows:The design structure and implementation of dual axis solar array drive mechanism are briefly introduced. A new maneuver mode that the satellite and the solar arrays rotate saperately is proposed to reduce the affection for the satellite attitude from flexible vibration during attitude maneuver. The attitude dynamic model of the satellite with dual axis solar array drive actuator is established for new maneuver mode by hybrid coordinate method and Lagrange theory.Then, the control system is analyzed, and negative feedback influence on the system by flexible vibration is studied. The dynamic model of traditional single axis satellite is established, and the PD plus feedforward control law is designed. Moreover, the simulation results of the roll maneuver control, pitch and yaw stabilization control are presented to validate the proposed control law.Finally, the new maneuver mode, the nonlinear feedback control law of satellite attitude maneuver and the solar array rotation is designed by the feedback linearization approach. The simulation is achieved for the synchronized and continous maneuver strategy of the rigid body and solar arrays. The comparision of control effect between the single axis and dual axis satellite is given. The results demonstrate that dual axis solar array mechanism takes adavantages in the flexible vibration suppression and attitude stability precision.