The attitude maneuver and stable task of a small satellite by using a Single Gimbal Control Moment Gyro(SGCMG) as an actuator was explored with the terminal sliding mode control method. Firstly, a small satellite mathematical model was established based on the Modified Rodrigues Parameters (MRP), and the torque planning was made in the terminal sliding mode control method. Then, command torque was given through diagonal singular robust tracking control law using the SGCMG as an actuator. The performance of the control method was studied by mathematical simulation, and the changing law and chosen rule of design parameters of the terminal sliding mode control were presented. Finally, a small satellite three-axis air flotation turntable was used to verify the adaptability of terminal sliding mode control. The experimental results show that the attitude angle and attitude angular velocity control precision and steady state error is less than 0.1 ° and 0.01(°)/s, which is within the scope of the best control precision from the parameter selection principle in the three-axis air flotation turntable for small satellite maneuver stability experiment. It concludes that the terminal sliding mode control method has high control precision and stability and is able to give a good function for small satellite maneuvers.