中国空间科学技术

中国空间科学技术 ›› 2024, Vol. 44 ›› Issue (4): 111-118.doi: 10.16708/j.cnki.1000-758X.2024.0062

• 论文 • 上一篇    下一篇

小行星探测器轨道计算的动力学研究

王宏，鄢建国，樊敏，李海涛   

  1. 1.北京跟踪与通信技术研究所，北京100094
    2.武汉大学 测绘遥感信息工程国家重点实验室，武汉430070
  • 出版日期:2024-08-25 发布日期:2024-07-26

Dynamics of asteroid probe orbit calculation

WANG Hong，YAN Jianguo，FAN Min，LI Haitao   

  1. 1.Beijing Institute of Tracking and Telecommunications Technology，Beijing 100094，China
    2.State Key Laboratory of Information Engineering in Surveying，Mapping and Remote Sensing，Wuhan University，Wuhan 430070，China
  • Published:2024-08-25 Online:2024-07-26

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摘要： 针对中国即将开展的小行星探测活动中面临的轨道计算动力学问题进行研究。分析了小行星探测器轨道计算的需求，并对小行星轨道计算中涉及的时空参考系进行了描述，然后对轨道计算所需考虑的动力学模型进行了讨论，并给出了各类摄动加速度的计算公式。最大的是太阳引力加速度，约为10-6km/s2；最小的是小行星本体摄动加速度，约为10-12～10-13km/s2。利用欧空局Rosetta探测器的实测数据对动力学模型精度进行了验证，结果表明4天弧段位置互差约15m，速度互差约0.44mm/s，动力学模型精度可靠。本研究可以为中国小行星探测活动轨道计算提供参考。

关键词: 小行星探测, 时空参考系, 轨道计算, 动力学模型, 引力场, 轨道摄动

Abstract: The problem of orbit calculation dynamics in the upcoming asteroid exploration missions of China is studied.The demand of asteroid probe orbit calculation is analyzed，and the space-time reference system involved in asteroid orbit calculation is described，then the dynamical models to be considered in orbit calculation are discussed.The calculation formulas of various types of perturbation acceleration are given.The largest force model is the gravitational acceleration of the Sun，with magnitude about 10-6km/s2，and the smallest is the asteroid body perturbation acceleration which is about 10-12-10-13km/s2.The difference between ephemeris of Rosetta provided by ESA and that integrated from the dynamical model in this paper shows that the four-day arc segment position error is about 15m，velocity error is about 0.44mm/s，so the accuracy of the dynamical model is reliable.The above study can provide a reference for the orbit calculation of China′s asteroid exploration missions.

Key words: asteroid exploration, space-time reference system, orbit calculations, dynamical models, gravitational field, orbit perturbation