月球探测器天文测角/单程无线电时间差分测距/差分测速导航方法

doi:10.7527/S1000-6893.2020.24531

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月球探测器天文测角/单程无线电时间差分测距/差分测速导航方法

宁晓琳¹, 梁晓钰², 吴伟仁^3,4, 房建成¹

1. 北京航空航天大学前沿科学技术创新研究院, 北京 100191;
2. 北京航空航天大学仪器科学与光电工程学院, 北京 100191;
3. 北京航空航天大学未来空天技术学院, 北京 100191;
4. 探月与航天工程中心, 北京 100037

收稿日期:2020-07-11 修回日期:2020-09-29 发布日期:2020-12-25
通讯作者: 梁晓钰 E-mail:liangxiaoyu17@buaa.edu.cn
基金资助:
国家自然科学基金（61722301）；空间智能控制技术重点实验室开放基金（ZDSYS-2017-04）

Lunar probe navigation based on celestial angle measurement, one-way radio time-differenced distance and time-differenced velocity measurement

NING Xiaolin¹, LIANG Xiaoyu², WU Weiren^3,4, FANG Jiancheng¹

1. Research Institute for Frontier Science, Beihang University, Beijing 100191, China;
2. School of Instrumentation and Optoelectronic Engineering, Beihang University, Beijing 100191, China;
3. School of Future Aerospace Technology, Beihang University, Beijing 100191, China;
4. Lunar Exploration and Space Engineering Center, Beijing 100037, China

Received:2020-07-11 Revised:2020-09-29 Published:2020-12-25
Supported by:
National Natural Science Foundation of China (61722301); Funded by Science and Technology on Space Intelligent Control Laboratory (ZDSYS-2017-04)

摘要/Abstract

摘要： 月球探测器高精度导航技术是确保月球探测任务顺利实施的关键技术之一。当前，大多数月球探测器都是利用地面无线电进行导航和控制，但存在可测控弧段短、易受干扰等局限性，且对于月球背面探测，存在无法直接测控的不足。针对上述问题，提出了一种新的基于天文测角/单程无线电差分测距/差分测速的月球探测器组合导航方法。该方法使用了天文星光角距、探测器接收到的来自地面站或中继星的单程无线电时间差分测距和时间差分多普勒测速3种量测信息，可有效抑制星上时钟和频谱仪的时间和频率测量误差。收敛后的平均位置和速度估计误差分别为902.7 m和0.12 m/s，最大的位置和速度估计误差分别为1 548.2 m和0.24 m/s。仿真分析结果表明该方法具有较高自主导航精度。

关键词: 月球探测导航, 天文测角, 时间差分, 无线电测距测速, 组合导航

Abstract: The high-precision navigation technology of the lunar probe is one of the key technologies to ensure the smooth implementation of the lunar exploration mission. Currently, most lunar probes depend on ground radio station for navigation and control, but have some limitations such as short measurable and controllable arcs and susceptibility to interferences. In addition, for the detection of the back of the moon, the lunar probes such as Chang'e-4 cannot be directly measured and controlled. To solve the above problems, a new integrated navigation method is proposed for the lunar probe. This method uses three types of measurement information:celestial angle measurement, one-way radio time-differenced distance measurement received from the ground station or relay satellite by the probe, and time-differenced Doppler velocity measurement. The method can effectively suppress the time and frequency measurement errors of the on-board clock and spectrum analyzer. The simulation analysis results show that the average position and velocity estimation errors after convergence of the method are 902.7 m and 0.12 m/s, respectively, and the maximum position and velocity estimation errors are 1548.2 m and 0.24 m/s, respectively, which means that this method has high autonomous navigation accuracy.

Key words: navigation of lunar exploration, celestial angle measurement, time difference, radio distance and velocity measurement, integrated navigation

中图分类号:

V448.21

宁晓琳, 梁晓钰, 吴伟仁, 房建成. 月球探测器天文测角/单程无线电时间差分测距/差分测速导航方法[J]. 航空学报, 2021, 42(11): 524531-524531.

NING Xiaolin, LIANG Xiaoyu, WU Weiren, FANG Jiancheng. Lunar probe navigation based on celestial angle measurement, one-way radio time-differenced distance and time-differenced velocity measurement[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(11): 524531-524531.

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Lunar probe navigation based on celestial angle measurement, one-way radio time-differenced distance and time-differenced velocity measurement

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