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在圆限制性三体问题框架内,针对不同类型平动点轨道的特点,提出一种基于优化算法的平动点轨道生成方法.通过设定轨道特征点,以轨道闭合程度为目标函数,使用优化算法寻找精确的初始状态,可得到闭合程度很高的平动点周期轨道;以航天器在限定区域自主运行时间为目标函数,使用优化算法将航天器状态不断修正到稳定流形上,理论上可得到任意时间长度的平动点拟周期轨道.这种方法简洁高效,通用性强,灵活性高,不需要使用任何解析方法即可得到多数典型类别的平动点轨道.将其应用到深空探测轨道任务中,将大大降低平动点轨道的计算难度,为平动点轨道设计提供一种新的思路.
In the framework of circular restricted three-body problem, aiming at the characteristics of different types of translational orbits, a method of generating translational point trajectories based on optimization algorithm is proposed. By setting the trajectory feature points and using the degree of orbit closure as the objective function, The optimization algorithm looks for the exact initial state and can get the periodic orbit of the translational point with a high degree of closure. Taking the spacecraft autonomous operation time in the limited area as the objective function, the optimization algorithm is used to modify the state of the spacecraft to a stable manifold. The theory Can be obtained for any period of translational pseudo-periodic orbit.This method is concise and efficient, versatile, high flexibility, without using any analytical method to get most of the typical class of translational point orbit.This method is applied to Deep space exploration orbit mission, will greatly reduce the computational complexity of translational orbit point, for the translation point orbit design provides a new way of thinking.