Abstract: In order to replace the real moving parts in the process of ground micro-vibration test, a six-dimensional excitation system that can be dynamically calibrated was designed to apply accurate excitation force/torque at any position of the spacecraft. Six single-axis output actuators were adopted in the space according to position constraints. Each actuator was equipped with a measuring unit to observe and calibrate the control signal of the actuator. Considering the influence of non-ideal factors and the flexibility of the adaptors, the actuator was calibrated both individually and in combination. The calibration results show that the self-calibration accuracy of the actuator is better than 0.4 N, and the difference among output characteristics of different actuators is less than 10%. Given the impact of the flexibility of the vibration isolation link, the control signal can be generated by trial and error selection of the optimal solution.