Study of Correction Maneuver for Lunar Flyby Transfers in the Real Ephemeris

Abstract

In this paper, the trajectory correction maneuver (TCM) problem of several lunar flyby transfers is investigated in the ephemeris model. The error analysis indicates that the state error of a transfer orbit will be enlarged by lunar flyby; hence, a TCM must be executed before lunar flyby. A TCM approach based on the shooting method is proposed in the ephemeris model. This method is then applied to design the TCM of two kinds of lunar flyby transfers: transfers between the sun–Earth/moon libration point orbits, and transfers from the Earth to the sun–Earth/moon libration point orbits. Some regions with abnormally large fuel costs are found and explained by the numerical method. Furthermore, several TCM strategies of lunar flyby transfers under practical constraints are presented and discussed. Finally, the effect of the navigation errors on the TCM problem is investigated.