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The rigid-flexible coupling dynamics model of a separated satellite with flexible cable is derived using Lagrange method. Based on the proposed model，the flexible cable effect on the vibration isolation performance and pointing control of the satellite is investigated. The simulation result indicates that the flexible cable decreases the vibration isolation performance at low frequencies. Furthermore ' the low frequency disturbances from the support module dramatically degrade the attitude accuracy and stability of the satellite. The flexible cable also has significant effect on the pointing control performance of the payload module. Using the same PD controller, the steady-state error of the payload module with flexible cable is 4 orders of magnitude larger than that of the payload module without flexible cable. It can be concluded that the performance of the payload module is seriously degraded by the flexible cable. The dynamics model in this paper is important on how to improve the modeling and control accuracy of the separated satellites. [ABSTRACT FROM AUTHOR]