The coupling-vibration of spacecraft with large ring-shaped deployable antenna induced by temperature variations during the spacecraft entering and leaving the Earth’s shadow was numercially analysized. The transient temperature field of large deployable antenna was solved using the finite element method, and a rigid-flexible coupling dynamic model was established for the coupling-vibration analysis. The results show that temperature gradient of the antenna itself is mainly between the light side and the backlight side, and with which the thermal response characteristic time of antenna can be estimated. Obvious thermally induced coupling-vibration of antenna structure and the satellite attitude can be observed. The method present in this paper can reasonably be used to predict the thermally induced coupling-dynamic of deployable satellite antenna system.