NEW DYNAMIC MODEL FOR LUNAR PROBE AND ITS APPLICATION TO QUASI-PERIODIC ORBIT ABOUT THE TRANSLUNAR LIBRATION POINT

A new dynamic model with the standard ephemerides that describes the relative motion of a lunar probe in a rotating coordinate system is presented. By using the ephemerides, the description for the real physical situation is more precise. Compared with other high-order models, the complexity of the proposed model is lower. More specifically, the proposed model considers the influences of direct and indirect Sun's perturbation, and the eccentricity of the Moon's orbit. It also provides a solution without a truncation error. Further, a lunar L2 quasiperiodic orbit design is presented as an application of the proposed model. The initial conditions are calculated by using the Lindstedt-Poincare technique. An iteration method which introduces the Sun's influence gradually and the differential correction are utilized to adjust the initial conditions.