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从低地球轨道到逆行地球同步轨道的月球引力辅助转移的特性。

Properties of the lunar gravity assisted transfers from LEO to the retrograde-GEO.

作者信息

He Bo-Yong, Ma Peng-Bin, Li Heng-Nian

机构信息

State Key Laboratory of Astronautic Dynamics (ADL), Xi'an Satellite Control Center, Xi'an, 710043, China.

出版信息

Sci Rep. 2021 Sep 22;11(1):18813. doi: 10.1038/s41598-021-98231-1.

DOI:10.1038/s41598-021-98231-1
PMID:34552140
原文链接:https://pmc.ncbi.nlm.nih.gov/articles/PMC8458437/
Abstract

The retrograde geostationary earth orbit (retro-GEO) is an Earth's orbit. It has almost the same orbital altitude with that of a GEO, but an inclination of 180°. A retro-GEO monitor-satellite gives the GEO-assets vicinity space-debris warnings per 12 h. For various reasons, the westward launch direction is not compatible or economical. Thereby the transfer from a low earth orbit (LEO) to the retro-GEO via once lunar swing-by is a priority. The monitor-satellite departures from LEO and inserts into the retro-GEO both using only one tangential maneuver, in this paper, its transfer's property is investigated. The existence of this transfer is verified firstly in the planar circular restricted three-body problem (CR3BP) model based on the Poincaré-section methodology. Then, the two-impulse values and the perilune altitudes are computed with different transfer durations in the planar CR3BP. Their dispersions are compared with different Sun azimuths in the planar bi-circular restricted four-body problem (BR4BP) model. Besides, the transfer's inclination changeable capacity via lunar swing-by and the Sun-perturbed inclination changeable capacity are investigated. The results show that the two-impulse fuel-optimal transfer has the duration of 1.76 TU (i.e., 7.65 days) with the minimum values of 4.251 km s in planar CR3BP, this value has a range of 4.249-4.252 km s due to different Sun azimuths in planar BR4BP. Its perilune altitude changes from 552.6 to 621.9 km. In the spatial CR3BP, if the transfer duration is more than or equal to 4.00 TU (i.e., 17.59 days), the lunar gravity assisted transfer could insert the retro-GEO with any inclination. In the spatial BR4BP, the Sun's perturbation does not affect this conclusion in most cases.

摘要

逆行地球静止轨道（retro - GEO）是一种地球轨道。它的轨道高度与地球静止轨道（GEO）几乎相同，但倾角为180°。一颗逆行地球静止轨道监测卫星每12小时对地球静止轨道资产附近的空间碎片发出预警。由于各种原因，向西的发射方向既不兼容也不经济。因此，通过一次月球借力从低地球轨道（LEO）转移到逆行地球静止轨道是优先选择。监测卫星从低地球轨道出发并仅通过一次切向机动插入逆行地球静止轨道，本文对其转移特性进行了研究。首先在基于庞加莱截面方法的平面圆形限制性三体问题（CR3BP）模型中验证了这种转移的存在性。然后，在平面CR3BP中计算了不同转移持续时间下的两次脉冲值和近月点高度。在平面双圆限制性四体问题（BR4BP）模型中，将它们在不同太阳方位角下的离散情况进行了比较。此外，还研究了通过月球借力的转移倾角可变能力以及太阳摄动下的倾角可变能力。结果表明，在平面CR3BP中，两次脉冲燃料最优转移的持续时间为1.76 TU（即7.65天），最小值为4.251 km/s，在平面BR4BP中，由于不同太阳方位角，该值范围为4.249 - 4.252 km/s。其近月点高度从552.6 km变化到621.9 km。在空间CR3BP中，如果转移持续时间大于或等于4.00 TU（即17.59天），月球引力辅助转移可以以任何倾角插入逆行地球静止轨道。在空间BR4BP中，在大多数情况下太阳摄动不影响这一结论。

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