Abstract: For the rigid spacecraft attitude tracking control problem with parameter uncertainties and external disturbances, a method of finite time adaptive integral sliding mode controller is proposed in this paper. A spacecraft attitude tracking model is described with quaternion. The basic principles of finite time method are introduced. Then, an integral sliding surface is designed with finite time method, which estimates bound of the disturbances and parameter uncertainties. The method has the characteristic of integral sliding mode method and finite time method. Simulation results show the fine performance of the controller.