月球椭圆冰冻轨道任务的轨道设计与优化

IF 3.4 2区 物理与天体物理 Q1 ENGINEERING, AEROSPACE
Haiyang Li , Wei Zhang , Yingjie Zhao , Donghua Wei , Junpo Niu , Huixin Zheng
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引用次数: 0

摘要

月球冰冻椭圆轨道(ELFO)是向月球南极提供中继和导航服务的首选轨道类型,但对月球冰冻椭圆轨道转移轨道的设计和优化研究较少。在工程应用中,地月转移轨道的升/降特性控制、弹道射击收敛成功率的提高、ELFO转移轨道的优化等都是需要解决的新问题。本文建立了一种系统的低轨道飞行器飞行轨迹设计方法。针对地月转移,提出了一种基于偏心矢量射击的双向积分模型,该模型求解过程简单,射击成功率高,能够精确控制轨道升/降特性。为了优化月球捕获到ELFO后的转移轨迹,提出了一种三冲量转移框架,并进行了参数偏移设计,以扩大设计空间。仿真结果验证了提出的偏心矢量射击双向积分模型成功控制了上升/下降特性,模拟射击成功率达到100%。三冲量传递框架可以有效地优化速度增量,实现对ELFO的插入。此外,冻结参数偏移被证明可以在保持轨道冻结特性的同时降低速度增量要求。本文提出的方法已成功地应用于中国天都卫星的在轨运行,这是首个在elfo运行的航天器,证实了所提出方法的有效性。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
Trajectory design and optimization for elliptical lunar frozen orbit mission
The elliptical lunar frozen orbit (ELFO) is the preferred orbit type for providing relay and navigation services to the lunar south pole, yet limited research exists on the design and optimization of transfer trajectories to ELFO. For engineering applications, several new challenges must be addressed, including the control over the ascending/descending characteristics of Earth-Moon transfer trajectories, the improvement of trajectory shooting convergence success rate, and the optimization of transfer trajectories to ELFO. A systematical trajectory design methodology for missions to ELFO is established in this paper. For the Earth-to-Moon transfer, a bidirectional integration model based on the eccentricity vector shooting is proposed, enabling precise control of trajectory ascending/descending characteristics with a simple solution process and high shooting success rate. For the optimization of transfer trajectories after lunar capture to ELFO, a three-impulse transfer framework is proposed, accompanied by a parameter offset design to expand the design space. Simulation results validate that the proposed bidirectional integration model with eccentricity vector shooting successfully controls ascending/descending characteristics, achieving a 100 % shooting success rate in simulations. The three-impulse transfer framework can effectively optimize the velocity increment and achieve the insertion to ELFO. Additionally, frozen parameter offset is demonstrated to reduce velocity increment requirements while preserving orbit frozen characteristics. The methodologies proposed herein have been successfully applied to the in-orbit operations of Chinese Tiandu satellite—the first spacecraft to operate in ELFO—confirming the effectiveness of the proposed methods.
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来源期刊
Acta Astronautica
Acta Astronautica 工程技术-工程:宇航
CiteScore
7.20
自引率
22.90%
发文量
599
审稿时长
53 days
期刊介绍: Acta Astronautica is sponsored by the International Academy of Astronautics. Content is based on original contributions in all fields of basic, engineering, life and social space sciences and of space technology related to: The peaceful scientific exploration of space, Its exploitation for human welfare and progress, Conception, design, development and operation of space-borne and Earth-based systems, In addition to regular issues, the journal publishes selected proceedings of the annual International Astronautical Congress (IAC), transactions of the IAA and special issues on topics of current interest, such as microgravity, space station technology, geostationary orbits, and space economics. Other subject areas include satellite technology, space transportation and communications, space energy, power and propulsion, astrodynamics, extraterrestrial intelligence and Earth observations.
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