Abstract
Chang’E-2 has firstly successfully achieved the flight mission which is from lunar orbit to Sun-Earth Lagrangian point L2 in the world. In this paper, we systematically investigate the trajectory design problem of this mission, and present the target Lissajous orbit of Sun-Earth L2 point based on the full ephemeris model. For complicated dynamics system of Sun-Earth-Moon, we design the low-energy transfer trajectory in double three-body system of Sun-Earth and Earth-Moon model using invariant manifolds theory. The results of flight test show that the tajectory design of Chang’E-2 mission is accurate and feasible.
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