基于月球借力的低能DRO入轨策略  

Lunar-gravity-assisted low-energy transfer from Earth into Distant Retrograde Orbit(DRO)

作　　者：张晨[1] 张皓 ZHANG Chen;ZHANG Hao(Technology and Engineering Center for Space Utilization,Chinese Academy of Sciences,Beijing 100094,China)

机构地区：[1]中国科学院空间应用工程与技术中心,北京100094

出　　处：《航空学报》2023年第2期268-279,共12页Acta Aeronautica et Astronautica Sinica

基　　金：国家重点研发计划(2018YFB1900605);中国科学院重点部署项目(ZDRW-KT-2019-1-0102);航天飞行动力学国家级重点实验室基金(6142210200302)。

摘　　要：在地月空间的远距离逆行轨道(DRO)部署月球轨道站可显著降低月球开发成本,并可作为未来小行星探测和载人火星任务的跳板。月球轨道站的在轨建造和货物补给任务中,提高航天器入轨质量是重要问题。从地球至DRO的转移轨道可以采用弱稳定边界(WSB)转移轨道降低入轨脉冲,但是直接抵达WSB需要较高的火箭发射脉冲。研究了基于月球借力的弱稳定边界DRO入轨策略,首先通过“近月点庞加莱图”和“v无穷匹配”获得较好的轨道初值,接着采用“多步打靶”在星历下对转移轨道进行修正,上述方法有效提高了该类型转移轨道的计算效率。对于共振比2∶1的DRO轨道,总脉冲最优解的地球发射脉冲3.127 km/s(与直接抵达WSB相比降低60~70 m/s),飞行总时间102.88 d,DRO入轨脉冲仅需66.1 m/s。Deploying the space station on a stable periodic orbit(e.g.,distant retrograde orbits,DROs)in the vicinity of the Moon can significantly reduce the lunar exploration cost,and the space station can also be used as a steppingstone for manned asteroid or mars missions.Reducing fuel consumption is an important issue during construction and cargo resupply of the cislunar station.For transter trajectory from Earth into DRO,DRO insertion cost can be effectively saved with the aid of weak stability Boundary(WSB)transfer,but reading WSB directly requires higher launch velocity.This paper aims at improving the numerical sensitivity of transfer trajectory which leverage Lunar Gravity Assist(LGA)and WSB transfer simnltaneously.The initial guess of trajectories are obtained by“perilune Poincare map”and“v infinity matching”strategies,then multiple shooting with analytic gradient is applied under high fidelity model,better computerational efficiency are obtained by applying improved methods.In numerical simulation,for the DRO with a resonant ratio of 2∶1,for the minimum cost solution,the Earth launching injection is 3.127 km/s(60-70 m/s is reduced compared with directly launching into WSB).The time of flight is 102.88 d,and DRO insertion maneuver only needs 66.1 m/s.

关 键 词：N体问题 DRO轨道 轨道优化 弱稳定边界 庞加莱截面 月球借力 

分 类 号：V412.41[航空宇航科学与技术—航空宇航推进理论与工程]