This article proposes the method for conducting thermal vibration analyses of the composite sandwich plate of a satellite in the space environment. Based on the continuous model, the method is derived using the Rayleigh-Ritz method and includes thermo-elastic coupling vibration by the space environment. In addition, the validity of the method is verified by the results of the finite element analysis and experimental analysis. Finally, parametric analysis is performed to investigate thermo-elastic coupling vibration characteristics of a satellite structure. This result allows a database to be design guidelines of composite sandwich structures for aerospace applications. We then concluded that the method is well-suited to thermally induced vibration analysis of a composite sandwich plate for aerospace applications due to their relative simplicity and computational efficiency.