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Due to the influence of the dynamic performance and steady-state accuracy of the current spacecraft wind tunnel test control system, the control error of the spacecraft center deviation from the wind tunnel axis is large, and the pressure of the upper rotor is inconsistent with the actual value. The overall structure of the control system is designed based on PROFIBUS. The servo motor module is used to control the start stop command, and the Siemens 57-300 PLC is used as the master station to design the field controller. A kind of support device for spacecraft wind tunnel test is developed, and the angle of attack mechanism is installed in the modular hierarchical structure. Using multi axis linkage controller, RS-232 serial communication principle, 2kW servo driver is selected according to the load inertia to realize the emergency stop of servo motor, and the hardware design of control system is completed. The flexible bang bang control is used to eliminate the influence of system dynamic performance and steady-state accuracy. With the support of error data, the experimental control process is designed and the control system software is designed. The experimental results show that the maximum deviation distance of the spacecraft center from the wind tunnel axis is 0.32mm, and the minimum is 0.1mm. The pressure of the upper rotor is consistent with the actual value, the control error is small, and the system has accurate control effect.