The distributed active vibration suppression program for great flexible spacecraft based on aptitude material

Abstract

For the spacecraft which has great flexibility and strong coupling has the large ground measurements error of flexible parameters and the high-precision in orbit control difficulties. Based on piezoelectric ceramic sensor and actuator we design the active vibration suppression program which obtains the dynamics model of spacecraft that has great flexibility through parameter identification of high-precision quality characteristics. By the analysis of the vibration characteristics the program can figure the characteristic points that can accurately reflect the vibration feature of spacecraft or restrain that. Then we can select the points which represent the flexible vibration feature of spacecraft. Through combining the vibration message obtained through piezoelectric sensors the attitude massage and parameters of control mechanism we can figure the mechanical parameter of flexible vibration and construct dynamic model. We design the piezoelectric ceramic actuators and reaction wheels as executive mechanism and fix multiple piezoelectric ceramic actuators on the vibration suppression points. The multiple piezoelectric ceramic actuators charge for the vibration suppression and the reaction wheels charge for the attitude control of spacecraft. Linear quadratic control method is used. We do the system verification on the air flotation platform. The result shows that the program can suppress the active vibration and achieve the high-precision control of great flexibility satellite.