小偏心率空间碎片天基短弧定轨方法和实验

doi:10.12305/j.issn.1001-506X.2022.08.25

系统工程与电子技术 ›› 2022, Vol. 44 ›› Issue (8): 2601-2611.doi: 10.12305/j.issn.1001-506X.2022.08.25

小偏心率空间碎片天基短弧定轨方法和实验

李大卫^1,^2,^3,*, 刘静^1,^2,³, 彭喜衍^1,², 张耀^1,^2,³, 解延浩⁴

1. 中国科学院国家天文台, 北京 100101
2. 国家航天局空间碎片监测与应用中心, 北京 100101
3. 中国科学院大学, 北京 100049
4. 长光卫星技术有限公司, 吉林长春 130033

收稿日期:2021-04-27 出版日期:2022-08-01 发布日期:2022-08-24
通讯作者: 李大卫
作者简介:李大卫(1985—), 女, 助理研究员, 博士研究生, 主要研究方向为短弧初始轨道确定、空间碎片监测预警|刘静(1970—), 女, 研究员, 博士, 主要研究方向为空间碎片监测预警技术系统论证|彭喜衍(1986—), 女, 助理研究员, 博士, 主要研究方向为空间碎片图像处理和高精度天文定位|张耀(1980—), 男, 高级工程师, 博士研究生, 主要研究方向为空间碎片监测预警|解延浩(1992—), 男, 研究实习员, 硕士, 主要研究方向为卫星姿态控制建模与仿真、卫星姿控传感器在轨标定、天基在轨目标观测与识别
基金资助:
国家自然科学基金(12073045);空间碎片科研项目(KJSP2020020205);空间碎片科研项目(KJSP2016020101);空间碎片科研项目(KJSP2016020201);空间碎片科研项目(KJSP2016020301);空间碎片科研项目(KJSP2016010101)

Initial orbit determination for a near-circular orbit of space debris with space-based short-arcs method and experiment

Dawei LI^1,^2,^3,*, Jing LIU^1,^2,³, Xiyan PENG^1,², Yao ZHANG^1,^2,³, Yanhao XIE⁴

1. National Astronomical Observatories, Chinese Academy of Sciences, Beijing 100101, China
2. Space Debris Observation and Data Application Center, China National Space Administration, Beijing 100101, China
3. University of Chinese Academy of Sciences, Beijing 100049, China
4. Chang Guang Satellite Technology Co., Ltd., Changchun 130033, China

Received:2021-04-27 Online:2022-08-01 Published:2022-08-24
Contact: Dawei LI

摘要/Abstract

摘要：

低轨空间碎片数量巨大, 对航天器在轨安全运行造成严重影响。天基光学是空间碎片观测的重要发展方向。低轨天基光学观测平台观测低地球轨道空间厘米级碎片的观测弧段相对较短, 由单个观测弧段难以确定目标的初始轨道, 初始轨道的误差也不容易评估。本文基于可行域方法, 建立了初始轨道确定和误差估计算法。针对天基短弧光学观测数据的初始轨道不易确定的问题, 本文提出了圆轨道辅助可行域方法。通过与商业遥感卫星合作, 利用遥感视频星开展了低轨空间碎片观测实验, 并利用天基实测数据对所提出的计算方法进行了验证, 为后续利用初始轨道进行弧段间关联奠定了基础。

关键词: 空间碎片, 天基短弧光学观测, 初轨确定, 初轨误差

Abstract:

The large amount of low earth orbit (LEO) space debris has a serious impact on the safe operation of orbital spacecraft. Space-based optical observation is the mainstream development direction for space debris observation. For centimeter sized space debris in LEO, the observable duration obtained by the LEO space-based telescope is relatively short. It is difficult to determine the initial orbit from the single arc of observation, and the error of the initial orbit is difficult to evaluate. Based on the admissible region method, this paper establishes the initial orbit determination and error estimation algorithm. Aiming at the problem that the initial orbit of space-based short-arc optical observation is not easy to be determined, this paper proposes a circular orbit auxiliary admissible region method. The LEO space debris observation experiment on commercial remote sensing satellites is carried out to verify the proposed calculation method, and to lay a foundation for the future research on observation-to-observation association using initial orbits.

Key words: space debris, space-based short-arc optical observation, initial orbit determination, error of initial orbit

中图分类号:

V412.41

李大卫, 刘静, 彭喜衍, 张耀, 解延浩. 小偏心率空间碎片天基短弧定轨方法和实验[J]. 系统工程与电子技术, 2022, 44(8): 2601-2611.

Dawei LI, Jing LIU, Xiyan PENG, Yao ZHANG, Yanhao XIE. Initial orbit determination for a near-circular orbit of space debris with space-based short-arcs method and experiment[J]. Systems Engineering and Electronics, 2022, 44(8): 2601-2611.

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参数	赤经/(°)	赤纬/(°)	赤经变率/((°)/s)	赤纬变率/((°)/s)
真值	286.879 987	-31.571 968	0.031 269	0.061 793
估计值	286.877 894	-31.572 847	0.031 315	0.061 872
置信区间下限(95%)	286.877 855	-31.572 906	0.031 289	0.061 823
置信区间上限(95%)	286.877 933	-31.572 789	0.031 343	0.061 903
偏差	2.08e-03	-8.89e-04	4.44e-05	7.78e-05

参数	半长轴/km	偏心率/(°)	轨道倾角/(°)	升交点赤经/(°)	近地点角/(°)	平近点角/(°)	近地点角+平近点角/(°)
真值	7 008.557	0.002	97.928	299.953	50.553	199.637	250.190
初始轨道	7 019.035	0.001	97.927	299.947	17.806	232.395	250.201
偏差	10.478	-0.001	-0.001	-0.006	-32.747	32.758	0.011
标准差	9.215	0.000	0.016	0.123	0.000	0.000	0.256

偏差项	半长轴/km	偏心率/(°)	轨道倾角/(°)	升交点赤经/(°)	近地点角/(°)	平近点角/(°)	近地点角+平近点角/(°)
真值	7 008.557	0.002	97.928	299.953	50.553	199.637	250.190
初始轨道	7 027.699	0.001	97.922	299.957	317.025	293.201	250.225
偏差	19.142	-0.001	-0.006	0.003	266.472	93.563	0.035
标准差	20.444	0.001	0.033	0.253	0.000	0.000	0.524

偏差项	半长轴/km	偏心率/(°)	轨道倾角/(°)	升交点赤经/(°)	近地点角/(°)	平近点角/(°)	近地点角+平近点角/(°)
真值	7 008.557	0.002	97.928	299.953	50.553	199.637	250.190
初始轨道	7 031.524	0.001	97.928	299.874	274.728	335.331	250.059
偏差	22.967	-0.001	0	-0.079	224.175	135.694	-0.131
标准差	47.979	0.003	0.080	0.583	0.000	0.000	1.214

偏差项	半长轴/km	偏心率/(°)	轨道倾角/(°)	升交点赤经/(°)	近地点角/(°)	平近点角/(°)	近地点角+平近点角/(°)
真值	7 008.557	0.002	97.928	299.953	50.553	199.637	250.190
圆轨道	7 017.755	0	97.949	299.780	0	249.738	249.738
偏差	9.198	-0.002	0.021	-0.173	-50.553	50.101	-0.452

小偏心率空间碎片天基短弧定轨方法和实验

Initial orbit determination for a near-circular orbit of space debris with space-based short-arcs method and experiment

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