Abstract: The averaged relative motion equation of elliptic orbit satellite formation is presented based on the averaged analysis method during an orbit period, and two different formation configuration maintaining methods are proposed. The orbit elements difference is used to derive the averaged relative motion equation, and the proposed model can effectively eliminate the periodic movement. Based on the linear recursive equation of mean orbit elements difference, the forecast equation of averaged relative motion is obtained via considering the orbital perturbation. The forecast model can provide valuable information for configuration design and configuration maintaining. Simulation results verify the effectiveness of the proposed formation configuration maintaining methods.

Key words: satellite, averaged relative motion, formation flying, configuration maintaining