Abstract: At first, based on kinematic relationship, motion equations of surrounding satel lite with respect to reference satellite is deduced under proper assumption. Then, specific formulas of generalized method of microsatellite formation flyin g configuration design are presented. Using this method, orbit elements of a ll the satellites in the formation can be solved directly, on condition that the reference orbit is a circular orbit or an elliptic orbit. At last, two typical examples of formation configuration design are given.