Abstract: On the orbit, a large flexible solar wing system of the space station would suffer a periodic thermal radiation and therefore a structural vibration. In order to investigate the influence of the mast's thermal control coating on the vibration, a sequential coupled thermal-structural analysis method is used to calculate the thermally induced vibration. For three different states of the mast's surface, that is, without coating, with electrodeposited coating and and with white paint coating, the displacement vs. time response is calculated correspondingly. The results show that the thermal control coating indeed has an influence on the thermally induced vibration, and the greatest mitigation effect is found for the case with the white paint coating.