| 小偏心率空间碎片天基短弧定轨方法和实验 |
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| 引用本文： | 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. DOI: 10.12305/j.issn.1001-506X.2022.08.25 |
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| 作者姓名： | 李大卫 刘静 彭喜衍 张耀 解延浩 |
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| 作者单位： | 1. 中国科学院国家天文台, 北京 1001012. 国家航天局空间碎片监测与应用中心, 北京 1001013. 中国科学院大学, 北京 1000494. 长光卫星技术有限公司, 吉林 长春 130033 |
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| 基金项目： | 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) |
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| 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。
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| 关 键 词： | 空间碎片 天基短弧光学观测 初轨确定 初轨误差 |
| 收稿时间： | 2021-04-27 |
Initial orbit determination for a near-circular orbit of space debris with space-based short-arcs method and experiment |
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| 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]. System Engineering and Electronics, 2022, 44(8): 2601-2611. DOI: 10.12305/j.issn.1001-506X.2022.08.25 |
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| Authors: | Dawei LI Jing LIU Xiyan PENG Yao ZHANG Yanhao XIE |
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| Affiliation: | 1. National Astronomical Observatories, Chinese Academy of Sciences, Beijing 100101, China2. Space Debris Observation and Data Application Center, China National Space Administration, Beijing 100101, China3. University of Chinese Academy of Sciences, Beijing 100049, China4. Chang Guang Satellite Technology Co., Ltd., Changchun 130033, China |
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| 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. |
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| Keywords: | space debris space-based short-arc optical observation initial orbit determination error of initial orbit |
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