A pointing and vibration isolation integrated control method for optical payload in the satellite system with a Pointing and Vibration Control Platform (PVCP) is developed and verified. Firstly, the dynamic model of the satellite system is formulated. This satellite system contains a payload, a PVCP and a satellite body. Three pointing control methods are proposed depending on different measurement information. By comparing the three methods, one reasonable control method is chosen for the pointing controller. This method could reduce the disturbance from the satellite body motion to the pointing control accuracy as well as the control error caused by the measurement accuracy of sensors. Then, the whole satellite attitude control loop is developed considering a rapid maneuver and rapid orientation mission. Finally, a series of verification experiments of the dynamic model of PVCP are carried out, and then the rotation accuracy, the stroke of PVCP, and the whole satellite attitude control loop are verified by numerical simulations. The results show that the pointing accuracy and attitude angular velocity of payload are improved using the integrated control method.