A Method for Calculating the Trajectory of a Single-Impulse Flight to a Halo Orbit around the L2 Libration Point of the Earth–Moon

Zhou Rui; Жуи Чжоу

doi:10.31857/S0023420623700152

A Method for Calculating the Trajectory of a Single-Impulse Flight to a Halo Orbit around the L2 Libration Point of the Earth–Moon

作者: Rui Z.¹
隶属关系:
1. Moscow Aviation Institute, 125080, Moscow, Russia
期: 卷 61, 编号 5 (2023)
页面: 382-392
栏目: Articles
URL: https://journals.rcsi.science/0023-4206/article/view/140380
DOI: https://doi.org/10.31857/S0023420623700152
EDN: https://elibrary.ru/PJVLGM
ID: 140380

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详细

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.

作者简介

Zhou Rui

Moscow Aviation Institute, 125080, Moscow, Russia

编辑信件的主要联系方式.
Email: 420790076@qq.com
Россия, Москва

参考

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