中国空间科学技术

中国空间科学技术

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星历模型下基于多重打靶拼接的长期近直线晕轨道

朱彦伟1,2,*，蒋昕玙3，陈昱桔1,2，郑清标4,5，王鹏5   

  1. 1.国防科技大学空天科学学院,长沙410073
    2.太空系统运行与控制全国重点实验室,长沙410073
    3.西北工业大学航天学院,西安710072
    4.航天工程大学宇航科学与技术系, 北京101400
    5.航天东方红卫星有限公司, 北京100094
  • 收稿日期:2025-07-24 修回日期:2025-08-25 录用日期:2025-09-10 发布日期:2026-04-09 出版日期:2026-04-09

Long-term NRHO design method based on multiple shooting segmentation under ephemeris model#br#

ZHU Yanwei1,2,*，JIANG Xinyu3，CHEN Yujie1,2，ZHENG Qingbiao4,5，WANG Peng5   

  1. 1.College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073,China
    2.State Key Laboratory of Space System Operation and Control, Changsha 410073, China
    3.School of Astronautics, Northwestern Polytechnical University, Xi'an 710072, China 4.Department of Aerospace Science and Technology, Space Engineering University, Beijing 101400, China
    5.DFH Satellite Co., Ltd., Beijing 100094, China
  • Received:2025-07-24 Revision received:2025-08-25 Accepted:2025-09-10 Online:2026-04-09 Published:2026-04-09

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摘要： 近直线晕轨道是地月空间航天器的一种典型任务轨道，其独特的动力学特性使得工程上需要设计出覆盖航天器寿命的长期稳定运行和低能耗保持轨道。针对高精度动力学模型下近直线晕轨道对初始参数敏感、数圈轨道后易发散等难点，提出了一种基于多重打靶拼接的长期近直线晕轨道设计方法，其基本原理是将轨道拆分为若干个可以用多重打靶进行星历模型转换的小段，分别将其用多重打靶转换至星历模型下，然后再利用多重打靶将其逐渐拼接起来，最终形成完整的长期星历参考轨道。在此基础上，通过基于靶点法的低能耗保持控制策略分析了长期轨道保持代价，进而可评估所设计轨道的性能。对L1、L2两种情况的仿真分析表明，所生成的近直线晕轨道持续时间能达到15年以上，年轨道维持代价工程上可以接受。所提出的设计方法适用于地月空间L1、L2的长期近直线晕轨道生成，满足航天器全寿命轨道设计要求。

关键词: 地月空间, 星历模型, 近直线晕轨道, 多重打靶法, 轨道设计

Abstract:

Near linear halo orbit is a typical mission orbit for spacecraft in cislunar space. Due to the unique dynamic characteristics, the long-term stable and low-energy maintenance orbit that covers the spacecraft full life is required in engineering. To address key challenges such as NRHOs’ sensitivity to initial parameters and their tendency to diverge after multiple revolutions under high-precision dynamic model, a long-term NRHO design method based on multiple-shooting segmentation is proposed. The core idea involves dividing the orbit into several segments that can be converted into anephemeris model using the multiple-shooting technique, and then gradually stitching them together to form a complete long-term reference orbit in the ephemeris model. Furthermore, a low-energy maintenance control strategy based on the target-point method is employed to analyze the long-term station-keeping cost, thereby enabling performance evaluation of the designed orbit. The simulation analysis of L1 and L2 scenarios shows that the generated nearly linear halo orbit can last for more than 15 years, and the annual orbit maintenance cost is acceptable in engineering. The proposed design method is applicable for the generation of long-term near linear halo orbits in cislunar space L1 and L2, meeting the requirements of spacecraft full life orbit design.

Key words: cislunar space, ephemeris model, near rectilinear halo orbits, multiple shooting, orbit design