Abstract: An acceleration control in the traditional vibration test by itself may induce a serious " over testing” problem. In view of the importance of the measurable interface force test in the engineering application of aerospace products, this paper proposes an indirect interface force monitoring method based on the voltage and the current of the moving coil of the electromagnetic shaking table. An interface force acquisition procedure is designed. Then the acceleration control based on the interface force assessment is implemented. This method is firstly verified by the simulated rigid mass model test, and then through the vibration test of two types of satellite-rocket locking devices, its effectiveness and practicability against the over testing are further proved. This study can be used for the detailed design and the test validation of the spacecraft payload.