Active Vibration Suppression Based On Component Synthesis Method For The Satellite With Double Flexible Sail

With the development of large scaled, agile and highly precise flexiblespacecrafts, the requirement of dynamics models are getting higher and higher modelaccuracy and control precision. However，rigid body motion of on orbit flexiblespacecraft will arouse elastic deformation of flexible accessory. For the lowenvironmental damping and the low structural damping of flexible material, it isdifficult to reduce the aroused vibration，and influence the control precision. Hence,research on dynamic model of flexible spacecraft and designing its attitude controlsystem has important significance.Flexible spacecraft dynamic modeling and vibration suppression for attitudemaneuver of flexible spacecraft has been studied in this thesis. The main contents andresults in this thesis are as follows:Based on the finite element theory, a model of structural dynamic characteristicsfor solar array is established. In this model, the solar panel is divided into somerectangular elements, the relationship of elastic displacement and node displacementarray are established.With the above mentioned flexible solar array, double flexible solar array satellitemodel is established. Dalembert method is applied to establish the dynamics model ofthe flexible spacecraft, and Lagrange method is used to establish the vibration modelof flexible accessory. The vibration model provides the basis to solve the activevibration suppression problem for the flexible spacecraft.Further exploration is done about the component synthesis vibration suppressing(CSVS) of the flexible spacecraft with flywheel. The component synthesis method iscompletely established to design the input voltage of flywheel controller. It is a wellperformance to realize the vibration suppression for the on-orbit satellite, and so thisthesis studies a control phenomena to adjust current peak value by designing the inputvoltage. The component synthesis method is applied to PD control method, and thesimulation results show that: the control strategy combining the component synthesismethod with PD control method gets a better performance comparing with PD control.In addition, if the component synthesis method is applied to the input of PD controller,it will be easier to design the controller of the PD method parameter and obtain higherattitude pointing accuracy and stability.