Abstract: In order to validate the tracking performance of the space electro-optical tracking system coupled with the satellite platform, a physical simulation test method is proposed in this paper. With a three-axis air-bearing platform simulating the free rotation of the three-axis stable satellite under zero gravity, the closed-loop tracking control characteristics of the non-cooperative target and the space coupled dynamics are simulated on the ground. The method of identifying the gravitational torque based on the whole-satellite attitude dynamics is adopted, to eliminate the influence of the rotational parts on the test, and to achieve an accurate evaluation of the system tracking. It is shown that the tracking accuracy of the non-cooperative target is better than 0.006°, which meets the need of the on-orbit applications. While in tracking the high-speed targets, the system has a certain phase lag, therefore, the control plan has to be further optimized.