Abstract

The problem of calculation of low-energy impulse trajectories to halo orbits in the vicinity of the L₂ point of the Earth–Moon system is considered. A new method for calculating the trajectories of a single-impulse low-energy flight to a halo orbit is presented. The limited problem of four bodies is analyzed, within which the attraction of the Earth, Moon, and Sun is taken into account, and their position and speed are calculated using high-precision ephemeris support. Particular attention in the development of the method is paid to ensuring its computational stability for calculating trajectories with a long stay of a spacecraft (SC) in the zone of weak stability near the boundary of the Hill sphere of the Earth. The results of the calculation of single-impulse transfer trajectories from low Earth orbit to halo orbit around the L₂ point of the Earth–Moon system are given. The analysis of the dependence of the main characteristics of single-impulse trajectories from the date of approach to the halo orbit is carried out.

中文翻译：

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地月系统L2平动点周围晕轨道单脉冲飞行轨迹计算方法

摘要

L ₂附近晕轨道的低能脉冲轨迹计算问题 考虑地月系统的点。提出了一种计算单脉冲低能飞行晕轨道轨迹的新方法。分析了四个天体的有限问题，其中考虑了地球、月球和太阳的吸引力，利用高精度星历支持计算它们的位置和速度。该方法的开发过程中特别注意确保其计算稳定性，以计算航天器（SC）在地球希尔球边界附近的弱稳定区域中长期停留的轨迹。_{近地轨道到绕L 2}晕轨道的单脉冲转移轨迹计算结果给出了地月系统的点。对接近晕轨道日期的单脉冲轨迹主要特征的依赖性进行了分析。