空间碎片半解析法轨道预报精度性能分析

李彬; 桑吉章; 宁津生

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空间碎片半解析法轨道预报精度性能分析

李彬, 桑吉章, 宁津生

文章导航 > 红外与激光工程 > 2015 > 44(11): 3310-3316

李彬, 桑吉章, 宁津生. 空间碎片半解析法轨道预报精度性能分析[J]. 红外与激光工程, 2015, 44(11): 3310-3316.

引用本文:

李彬, 桑吉章, 宁津生. 空间碎片半解析法轨道预报精度性能分析[J]. 红外与激光工程, 2015, 44(11): 3310-3316.

Li Bin, Sang Jizhang, Ning Jinsheng. Analysis of accuracy in orbit predictions for space debris using semianalytic theory[J]. Infrared and Laser Engineering, 2015, 44(11): 3310-3316.

Citation:

Li Bin, Sang Jizhang, Ning Jinsheng. Analysis of accuracy in orbit predictions for space debris using semianalytic theory[J]. Infrared and Laser Engineering, 2015, 44(11): 3310-3316.

空间碎片半解析法轨道预报精度性能分析

1.
武汉大学测绘学院,湖北武汉 430079;
2.
地球空间信息技术协同创新中心,湖北武汉 430079

基金项目:

国家自然科学基金(41474024);国家测绘地理信息局测绘基础研究基金(14-02-06)

详细信息

作者简介:
李彬(1988-),男,博士生,主要从事空间碎片精密轨道确定与预报研究。Email:libin@whu.edu.cn

中图分类号: P228

Analysis of accuracy in orbit predictions for space debris using semianalytic theory

1.
School of Geodesy and Geomatics,Wuhan University,Wuhan 430079,China;
2.
Collaborative Innovation Center for Geospatial Technology,Wuhan 430079,China

摘要: 针对数以万计的空间碎片,进行快速、精确的轨道确定与预报,以提供可靠的空间碰撞预警是当前空间态势感知的一个重要研究方向。半解析卫星/空间碎片轨道积分,可以克服轨道积分中数值法耗时、解析法低精度的不足。讨论了已初步研发成功的利用多尺度摄动原理的半解析轨道积分器及其在空间碎片轨道预报中的精度性能,并以精密数值积分结果作为真轨道评估半解析轨道积分器的精度。大量数据处理结果表明:面质比0.01、轨道高度300 km的碎片,预报1天,耗时不足60 ms,精度2 km左右,且随高度增加,预报精度更高,当高度超过1 000 km时,1天的预报精度仅为50 m左右,满足许多精密空间应用的要求。
- 空间碎片 /
- 半解析轨道积分器 /
- 轨道预报 /
- 大气阻力
Abstract: For tens of thousands of Earth orbiting space debris, fast and accurate orbit determination and prediction information is essential for providing reliable collision warnings, and thus becomes an important subject in the space situational awareness(SSA). To overcome the problems of low computing efficiency using numerical integration methods and large orbit prediction errors with analytical theories, semianalytic satellite theory(SST) that could achieve the accuracy of numerical methods with the computing efficiency of analytic methods was developed. The semianalytic orbit integrator being developed using the multi-scale perturbation method at Wuhan University was discussed, together with its prediction performace. Orbits generated from the precise numerical integrator was used as the true orbit to compute the prediction error of the developed semianalytic integrator. Preliminary results show that, for space objects with Area-to-mass ratio 0.01 and orbit altitude 300 km, 2 km prediction accuracy for 1-day orbit prediction is achieved using the semianalytic orbit integrator, and the computation time was only 60 ms.For orbits higher than 1 000 km in altitude, the prediction errors were mostly less than 50 m, meeting the requirements for many space applications.
- space debris /
- semianalytic orbit integrators /
- orbit prediction /
- atmospheric drag

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空间碎片半解析法轨道预报精度性能分析

1. 武汉大学测绘学院,湖北武汉 430079;

2. 地球空间信息技术协同创新中心,湖北武汉 430079

作者简介:
李彬(1988-),男,博士生,主要从事空间碎片精密轨道确定与预报研究。Email:libin@whu.edu.cn

收稿日期: 2015-03-05
修回日期: 2015-04-10
刊出日期: 2015-11-25

基金项目:

国家自然科学基金(41474024);国家测绘地理信息局测绘基础研究基金(14-02-06)

中图分类号: P228

关键词:

摘要: 针对数以万计的空间碎片,进行快速、精确的轨道确定与预报,以提供可靠的空间碰撞预警是当前空间态势感知的一个重要研究方向。半解析卫星/空间碎片轨道积分,可以克服轨道积分中数值法耗时、解析法低精度的不足。讨论了已初步研发成功的利用多尺度摄动原理的半解析轨道积分器及其在空间碎片轨道预报中的精度性能,并以精密数值积分结果作为真轨道评估半解析轨道积分器的精度。大量数据处理结果表明:面质比0.01、轨道高度300 km的碎片,预报1天,耗时不足60 ms,精度2 km左右,且随高度增加,预报精度更高,当高度超过1 000 km时,1天的预报精度仅为50 m左右,满足许多精密空间应用的要求。

English Abstract

Analysis of accuracy in orbit predictions for space debris using semianalytic theory

1. School of Geodesy and Geomatics,Wuhan University,Wuhan 430079,China;

2. Collaborative Innovation Center for Geospatial Technology,Wuhan 430079,China

Received Date: 2015-03-05
Rev Recd Date: 2015-04-10
Publish Date: 2015-11-25

Keywords:

Abstract: For tens of thousands of Earth orbiting space debris, fast and accurate orbit determination and prediction information is essential for providing reliable collision warnings, and thus becomes an important subject in the space situational awareness(SSA). To overcome the problems of low computing efficiency using numerical integration methods and large orbit prediction errors with analytical theories, semianalytic satellite theory(SST) that could achieve the accuracy of numerical methods with the computing efficiency of analytic methods was developed. The semianalytic orbit integrator being developed using the multi-scale perturbation method at Wuhan University was discussed, together with its prediction performace. Orbits generated from the precise numerical integrator was used as the true orbit to compute the prediction error of the developed semianalytic integrator. Preliminary results show that, for space objects with Area-to-mass ratio 0.01 and orbit altitude 300 km, 2 km prediction accuracy for 1-day orbit prediction is achieved using the semianalytic orbit integrator, and the computation time was only 60 ms.For orbits higher than 1 000 km in altitude, the prediction errors were mostly less than 50 m, meeting the requirements for many space applications.