Calculation of Inertial Forces Caused by Reference Frame Motion in Orbital Integration

The inertial forces caused by the reference frame motion are considered in the integra-tion of the satellite motion equations under the J2000.0 mean equatorial reference frame, the true equatorial reference frame and the orbital reference frame of J2000.0 mean equinox. The numerical integration is made by adding the inertial forces to the motion equations. A set of the state vecters on Jan.1st, 1994 is used to integrate the motion equations for one month. It is shown that the geocentric range and the velocity modulus are accordant to 30cm and 0.001 cm/s respectively.