Abstract: Due to the existing of various moving parts, the smaller amplitude and lower frequency will appear in the structure of spacecraft, when a spacecraft moving in orbit. This phenomenon will affect the inner payload. As an attitude measurement equipment of spacecraft, FOG obtains the characteristics of high bandwidth. Thus it was put forward that FOG can be adopted to measure the micro vibration. Moreover, EMD was adopted to decompose the output signal of FOG to intrinsic mode function on time scale as well. After that, Hilbert analysis method will be used to detect available micro vibration information. This method was tested in the spacecraft examination. The result shows that empirical mode decomposition technique could realize spacecraft's micro vibration, which brings a new method for the field of micro vibration measurement of spacecraft.