The invention discloses a periodic orbit escape method by utilizing near-earth-moon balance points, and belongs to the technical field of aerospace. The implementation method comprises the following steps: establishing an earth-moon rotating coordinate system and three-body dynamics, and solving a state transition matrix characteristic root and a characteristic vector of a periodic orbit; formingan unstable manifold through a periodic orbit near the balance point, selecting the unstable manifold close to the moon, solving deorbiting maneuver through differential correction, obtaining a transfer orbit meeting the requirement of the near-moon point constraint, and enabling the detector to apply corresponding maneuver to enable the detector to be transferred to the near-moon point. Near-moonpoint maneuver is solved through differential correction, a moon-ground transfer orbit meeting near-site constraints is obtained, the application maneuver makes full use of the gravitation effect ofthe moon, and the detector applies corresponding maneuver to transfer the detector to a near site. According to the escape speed requirement, the detector applies maneuver on the near site again, theapplied maneuver fully utilizes the earth-moon gravitation effect, and the speed increment of the detector escaping from the periodic orbit to the earth-moon system is reduced.
本发明为公开的一种利用地月旁近的平衡点周期轨道逃逸方法,属于航空航天技术领域。本发明实现方法:建立地月旋转坐标系和三体动力学,求解周期轨道的状态转移矩阵特征根和特征向量。通过平衡点附近的周期轨道生成不稳定流形,选择靠近月球的不稳定流形,利用微分修正求解离轨机动,获得满足近月点约束的转移轨道,探测器施加相应机动使探测器转移至近月点。利用微分修正求解近月点机动,获得满足近地点约束的月地转移轨道,施加机动充分利用月球的引力作用,探测器施加相应机动使探测器转移至近地点。根据逃逸速度需求,探测器在近地点再次施加机动,施加机动充分利用地月的引力作用,降低探测器从周期轨道逃逸地月系统的速度增量。
Periodic orbit escape method by utilizing near-earth-moon balance points
一种利用地月旁近的平衡点周期轨道逃逸方法
2020-10-02
Patent
Electronic Resource
Chinese
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