Abstract: The orbit control technology of two long-distance satellites with similar semi-major axis,eccentric angle and inclination RAAN was analyzed.First,a new method of controlling the swing of orbit normal axis by changing the semi-major axis to adjust the change rate of RAAN was studied;secondly,the relationship between the control time and the size of relative ellipse was given;thirdly,the method of estimating the parameter of the relative ellipse by the module difference of radial vector was put forward;finally,the proposed methods were verified by the long-distance approaching and companion flying simulation of SZ-7 companion satellite and orbital module.