This paper develops a re-entry attitude control method of a Spacecraft by sliding mode control (SMC) theory. The controller utilizes two-loop SMC scheme and provides robust, de-coupled tracking of both the angular velocity and orientation angles of the Spacecraft. And pointing to the blending controlling characteristic of the aerodynamic surfaces and reaction control system of the Spacecraft, allocating the control torque commands into the actuators such as the aerodynamic surfaces and reaction control system by the optimal control logic selection allocation algorithm. Simulation of the Spacecraft re-entry attitude controlling demonstrates robust, de-coupled tracking performance of this method and its validity.