For the short-range hover control of tracking spacecraft during rendezvous and docking,a linear sliding mode control law is designed based on the coupled attitude and orbit dynamics.To constrain the system state during the system convergence,an attitude and orbit coupled controller is developed with prescribed performance.Furthermore,a new finite time convergence performance function is used in the design of prescribed performance control law,and the sliding mode controller is improved in structure,with the purpose to reduce the system state convergence time.Finally,simulations and comparisons are given to verify the effectiveness of the designed spacecraft control law.