Abstract: The micro-vibration of ultra-high-static and ultra-high-stable spacecraft was studied. A modeling and simulation method was proposed to introduce the pointing measurement error and additional torque error induced by micro-vibration into the pointing measurement control system. The micro-vibration experiment of the pointing measurement system was carried out based on the quasi-zero stiffness suspension method. The simulation and experimental results show that the pointing measurement error induced by micro-vibration was more significant, and the peak value reached 10e-4°, and the pointing measurement error of the pointing control system caused by micro-vibration was 0.03 pixels. This work can be used for reference in the study of ultra-high-static and ultra-high-stable spacecraft and derivative technologies.