航天器太阳圆面速度差/太阳视方向组合导航

doi:10.7527/S1000-6893.2020.24253

电子电气工程与控制

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航天器太阳圆面速度差/太阳视方向组合导航

宁晓琳¹, 黄玉琳², 晁雯²

1. 北京航空航天大学前沿科学技术创新研究院, 北京 100083;
2. 北京航空航天大学仪器科学与光电工程学院, 北京 100083

收稿日期:2020-05-20 修回日期:2020-05-30 出版日期:2020-09-15 发布日期:2020-06-04
通讯作者: 宁晓琳 E-mail:niangxiaolin@buaa.edu.cn
基金资助:
国家自然科学基金（61722301）；中央高校基本科研基金（YWF-19-BJ-J-82）

Integrated navigation of solar disk velocity difference and sun direction for spacecraft

NING Xiaolin¹, HUANG Yulin², CHAO Wen²

1. Research Institute for Frontier Science, Beihang University, Beijing 100083, China;
2. School of Instrument Science and Opto-electronics Engineering, Beihang University, Beijing 100083, China

Received:2020-05-20 Revised:2020-05-30 Online:2020-09-15 Published:2020-06-04
Supported by:
National Natural Science Foundation of China (61722301); the Fundamental Research Funds for the Central Universities(YWF-19-BJ-J-82)

摘要/Abstract

摘要： 针对航天器，尤其是深空探测器的自主导航问题，提出了一种新的太阳圆面速度差天文量测信息，该信息利用太阳的较差自转所造成的太阳圆面各点速度不同的特性，是探测器当前位置的函数，其几何本质是一个探测器的位置圆锥。在此基础上，基于太阳圆面速度差和太阳视方向互补的特性，提出了一种太阳圆面速度差/太阳视方向组合导航新方法，将太阳圆面速度差与太阳视方向2种量测量结合起来，实现了量测量之间的优势互补，进一步提高了导航性能。以太阳探测器为例进行了仿真，仿真结果表明相比较于单独用太阳圆面速度差或太阳视方向的导航方法，基于太阳圆面速度差/太阳视方向的组合导航方法精度分别提升了10.2%和16.0%。此外，还分析了光谱仪精度、采样周期和光谱仪数量对导航性能的影响，为深空探测自主导航提供了新的理论与方法。

关键词: 太阳探测器, 太阳圆面速度差, 太阳视方向, 组合导航, 自主导航

Abstract: For autonomous navigation of spacecraft, especially in deep space exploration, a novel type of astronomical measurement information of the solar disk velocity difference is proposed. Utilizing the characteristics of the different velocities of the solar disk caused by the solar differential rotation, this information is a function of the current position of the explorer, with its geometric essence being a position cone of the explorer. Based on this and the physical law that the velocity difference of the solar disk and the line-of-sight vector of the sun complement each other, a novel navigation method integrating the solar disk velocity difference and the sun direction is proposed. It combines the two measurements of the velocity difference of the solar disk and the sun direction to achieve mutual complementation and further improve the navigation performance. This study uses the solar explorer as an example for simulation, and the results show that the accuracy of the combined navigation method is improved by 10.2% and 16.0% respectively compared with the navigation methods of using the solar disk velocity difference or the line-of-sight vector of sun alone. In addition, the impact of the spectrometer accuracy, the sampling time, and the number of spectrometers on the navigation performance is analyzed, providing a new approach to autonomous navigation of deep space exploration.

Key words: solar explorers, velocity difference of solar disk, sun direction, integrated navigation, autonomous navigation

中图分类号:

V249.32+8

宁晓琳, 黄玉琳, 晁雯. 航天器太阳圆面速度差/太阳视方向组合导航[J]. 航空学报, 2020, 41(9): 324253-324253.

NING Xiaolin, HUANG Yulin, CHAO Wen. Integrated navigation of solar disk velocity difference and sun direction for spacecraft[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2020, 41(9): 324253-324253.

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E-mail：hkxb@buaa.edu.cn

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

航天器太阳圆面速度差/太阳视方向组合导航

Integrated navigation of solar disk velocity difference and sun direction for spacecraft

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