宇航学报

宇航学报 ›› 2021, Vol. 42 ›› Issue (3): 284-294.doi: 10.3873/j.issn.1000-1328.2021.03.003

• 飞行器设计与力学 • 上一篇    下一篇

太阳系边际探测飞行任务规划

田百义，王大轶，张相宇，周文艳，朱安文，黄美丽，王颖
  

  1. 北京空间飞行器总体设计部，北京 100094

  • 收稿日期:2020-02-13 修回日期:2020-06-22 出版日期:2021-03-15 发布日期:2021-03-15

Flight Mission Planning for Solar System Boundary Exploration

TIAN Bai yi,WANG Da yi,ZHANG Xiang yu,ZHOU Wen yan,ZHU An wen,HUANG Mei li,WANG Ying   

  1. Beijing Institute of Spacecraft System Engineering, Beijing 100094, China
  • Received:2020-02-13 Revised:2020-06-22 Online:2021-03-15 Published:2021-03-15

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摘要： 针对太阳系边际探测任务，开展了星际多目标飞越的任务规划，采用小推力混合优化设计方法完成了基于借力飞行及电推进技术的行星际转移轨道联合优化设计，对比研究了面向日球层鼻尖和尾部探测的星际多目标探测飞行方案。研究表明，探测器在2024-2025年发射，可飞抵日球层鼻尖区域，在2027-2030年发射可飞抵日球层尾部区域，并可在2049年1月1日前飞离日心100 AU，实现太阳系边际空间的科学探测。其中日球层鼻尖探测任务探测器飞抵100 AU的位置位于鼻尖中心区域，可与旅行者1号、2号探测器形成有效互补。文章所用任务规划方法，可为太阳系边际探测的自主任务规划技术提供基础，相关研究成果能够为未来中国首次太阳系边际探测任务的实施提供有价值的参考。

关键词: 太阳系边际, 日球层, 小推力, 任务规划, 轨道优化, 多次借力

Abstract: Mission planning of interplanetary multi objective flyby is carried out for solar system boundary exploration, and the optimization of low thrust interplanetary transfer orbit combined with planet gravity assistance is completed. Based on the above research, the interplanetary flight schemes for the exploration of the tip and tail of the heliosphere are given. The results show that a probe launched during 2024-2025 and 2027-2030 can arrive at about 100 AU from the solar center before 2049, and touch the nasal tip and tail of the heliosphere. Among them, the tip explorer is located in the central region of the nose tip when it flies to the distance of 100 AU, which can effectively complement the Voyager 1 and Voyager 2. The mission planning method used in this paper can provide the basis for the autonomous mission planning technology of solar system boundary exploration, and the relevant research results can provide valuable reference for the implementation of the first solar system boundary exploration mission in China in the future.

Key words: Solar system boundary, Heliosphere, Low thrust; Mission planning, Trajectory optimization, Multiple gravity assistance

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