Abstract: In order to comprehensively analyze the adverse effects of flywheel micro-vibration on high-resolution optical remote sensing small satellite system, a full-link integrated analysis model for optical-attitude control-structure was established to evaluate the suppression of micro-vibration by the vibration isolation system in the design stage and to calculate the integrated image offset of the camera. Firstly, a two-stage vibration isolation dynamics model was built with flywheel vibration as input. Then, the image offset of the linear optical system as a function of the mirror body’s degrees of freedom was created, a simplified model of the satellite attitude control system was constructed, and the steady-state error of the satellite attitude angular velocity and image offset under vibration isolation were calculated. Finally, ground measurements and on-orbit micro-vibration verification were carried out. The results show that the maximum value of image offset calculated by the integrated analysis model is 0.129 8 px with a satellite attitude stability of 7.5×10^-6 rad/s under the action of the disturbance moment; the maximum value of single-direction image offset of the ground measurement in the frequency domain is 0.114 8 px with a satellite attitude stability of 7.5×10^-6 rad/s; and the maximum value of image offset of the on-orbit imaging in the frequency domain is 0.084 6 px with a satellite attitude stability of 7.0×10^-6 rad/s. The modeling and testing results are at the same level, which verifies the effectiveness of the model.