The Design And Experimental Analysis Of Piezoelectric-based Vibration Control System For Solar Panels

With the continuous development of space exploration, larger scale and lower weight are new requirements of spacecraft, the solar wing and antenna shows more and more flexible. On the other hand, the high precision of orientation and deep space observation require high performance of attitude control and small vibration etc.. Under the background of this demand, the dynamic properties of flexible attachment, especially the flexible attachment vibration disturbance of spacecraft if particularly disturbance is particularly important. In order to improve the precision of attitude control of the spacecraft, the dynamics of flexile attachment needs to be deeply analyzed and the coupling effect need to be studied, on this basis, the vibration suppression of flexible structure can come true.Vibration suppression can be realized in a passive or active way. Passive vibration suppression increases the stiffness of flexible attachment by improving the material or structure. Also it can reduces the incentive for the flexible attachment by changing the attitude maneuver control strategy. The efficiency of passive vibration suppression is limited, so people put forward the active vibration suppression method. Actuators and sensors are installed on the flexible attachment. The sensors are sensitive to the distortion of the flexible attachment, and the actuators an eliminate or reduce the distortion of the flexible attachment, so as to achieve the aim of the vibration control of flexible attachment.There are many theoretical research of the flexible vibration suppression technology based on piezoelectric element, and also experimental verifications. The base frequencies of structure in the experiments are high. Vibration suppression technology research is less in view of the large flexible structure of the low-frequency. This paper analyzed the structure of such large solar panels. A simplified finite element model of the flexible laminated plate is established. The patch position of the piezoelectric elements on the flexible laminated plate according to the Maximum strain criterion is designed. The form of transfer function from piezoelectric actuators to piezoelectric sensors and the transfer function under the existing of truncated form are identified. According to the transfer function, a new control system structure is designed in order to suppression the whole plate vibration. A control system is designed based on positive position feedback control law. Structural dynamics and control simulation model is established. The ability of the PPF control system on pate vibration suppression has carried on the appraisal under three kinds of disturbance input using this model. The effectiveness of PPF control law is verified on large flexible structure. The flexible structure vibration suppression test platform project has been put forward. A test platform has been set up. Adopted by the actual situation of plate structure, a non-contraposition PPF control system is proposed and it can suppress the vibration of the structure. The test results show that in the non-contraposition cases, in view of the large flexible structure, PPF controller has the certain control effect.