Abstract: Large deployable mesh antennas will be used increasingly in the spacecraft. Not only the size of the antenna increases more and more,but also the technical requirement becomes even tighter. The mechanical motions coming from attitude control,orbit control,solar array rotating inevitably result in vibrations of large reflector structure and lead to reducing the electrical performance of the antenna and the quality of the mission. A rigid-flexible-attitude control integrated analysis method is presented. The integrated simulation model consists of disturbance,rigid-flexible coupling dynamic model,attitude control,and antenna vibration effect analysis. Under the typical operating disturbance modes of the satellite,the computations of the vibration responses,the whole antenna pointing and the distortion level of the antenna structure are carried out. The analysis results will support the antenna in-orbit vibration effect analysis,performance index prediction,and vibration transfer mechanism analysis and vibration control measures.