Research On Distributed Vibration Control Method Of Large Flexible Spacecraft Solar Panels

At present,with the rapid development of the national space industry,the research of various key technologies of spacecraft has gradually broken through,and the structure of spacecraft has shown a trend of large scale and flexibility.The vibration of flexible structural components such as large flexible solar panels can easily cause the attitude motion of spacecraft central rigid body,which affects the execution of in-orbit tasks,and even causes the failure of spacecraft central rigid body payloads and mission failure.Therefore,it is of great significance to study the vibration control method of spacecraft flexible solar array.The research on the distributed vibration control method of spacecraft flexible solar panels is conducted in this paper,mainly including the following four aspects:Firstly,the actuality of in-orbit vibration control for spacecraft with large flexible components is analyzed.Then,the dynamic model of spacecraft large flexible solar panels with the piezoelectric ceramic actuators is established by using global modal modeling method.And asymmetric Bouc-Wen model is used to fit the hysteresis characteristics of piezoelectric ceramics.Then the parameters are optimized by genetic algorithm.Meanwhile two existing common control methods are analyzed: centralized control method and distributed control method based on LQR controller.The two control methods are applied to the vibration suppression of the solar panels with the same parameters using Simulink model to verify the superiority of the distributed control method applied to the large flexible structure.Secondly,the large flexible solar panel of the spacecraft is divided into 32 positions for actuator and sensor installation.According to the established model of the large flexible solar panel,the more versatile criterion of the optimal configuration based on the maximum controllability/observability degrees is used to find the installation position of the 8 sets of actuators and sensors.The calendar and genetic algorithm are respectively used to carry on the optimization calculation.The optimal solution of two cases with and without alternative installation position is obtained.By comparing and analyzing the optimization results,it is verified that the system controllability and observability are better when the actuator and sensor installation position are selected without alternative installation position.Then,considering the coupling effect of control force and vibration produced by adjacent control sub-modules,a distributed control method is designed for the large flexible solar panel system.According to Lyapunov stability theory,the stability of the control system is verified.The Simulink model is established and compared with the two control methods analyzed in this paper to verify the superiority and correctness of the control method designed in this paper.The hysteresis characteristics of piezoelectric ceramic actuator were controlled by feedforward compensation to avoid the error caused by voltage rise and drop in the control process,and a Simulink model was established to verify the accuracy of feedforward compensation control.Finally,a virtual prototype model of solar panel was established in Recur Dyn software,and the co-simulation of Simulink and Recur Dyn was adopted to verify the control performance of the proposed control method.The simulation was compared with the situation that the actuator and sensor position layout was not optimized.Verify that the actuator and sensor installation position designed in this paper has a favorable influence on the control effect.Then the distributed control method designed in this paper is compared with other control methods.So as to further verify the correctness and superiority of the control method designed in this paper.