嫦娥二号日地拉格朗日L2点探测轨道设计与实施

Design and performance of exploring trajectory to Sun-Earth L2 point for Chang’E-2 mission

嫦娥二号在国际上首次成功实现了从月球环绕轨道飞向日-地拉格朗日L2点的飞行任务.本文系统地研究了该任务的轨道设计问题,提出了高精度星历模型下日-地拉格朗日L2点附近Lissajous目标轨道的设计方案;针对复杂日-地-月系统动力学环境,基于非线性动力系统流形等理论,提出了日-地与地-月双三体系统下的低能量转移轨道方案.飞行试验结果证明了嫦娥二号日-地拉格朗日L2点探测轨道设计方案的正确性和可行性.

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.