基于轨道根数的低轨卫星轨道预测算法

李丹; 于洋

doi:10.3788/OPE.20162410.2540

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基于轨道根数的低轨卫星轨道预测算法

信息科学 | 更新时间：2020-07-07

- 基于轨道根数的低轨卫星轨道预测算法
- Prediction algorithm of close-orbit satellite based on orbit elements
- 光学精密工程 2016年24卷第10期页码：2540-2548
- 作者机构：
  
  中国科学院长春光学精密机械与物理研究所, 吉林长春 130033
- 作者简介：
  
  李丹(1981-),女,吉林长春人,助理研究员,2004年于吉林大学获得学士学位,2010于中国科学院研究生院获得硕士学位,主要从事电子学设计和开发的工作。E-mail:lidan981@sina.com
  [ "于洋(1981-),男,吉林长春人,博士研究生,助理研究员,2004年于中国科学技术大学获得学士学位,2006年于中国科学院研究生院获得硕士学位,主要从事图像处理,轨道预报技术的研究。E-mail:repusnam@163.com" ]
- 基金信息：
  
  国家自然科学基金资助项目(61308050)
- DOI：10.3788/OPE.20162410.2540
  中图分类号： V423.4
- 收稿日期：2016-01-15，
  
  录用日期：2016-3-1，
  
  纸质出版日期：2016-10
- 稿件说明：
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李丹, 于洋. 基于轨道根数的低轨卫星轨道预测算法[J]. 光学精密工程, 2016,24(10):2540-2548.

Dan LI, Yang YU. Prediction algorithm of close-orbit satellite based on orbit elements[J]. Optics and precision engineering, 2016, 24(10): 2540-2548.
李丹, 于洋. 基于轨道根数的低轨卫星轨道预测算法[J]. 光学精密工程, 2016,24(10):2540-2548. DOI： 10.3788/OPE.20162410.2540.

Dan LI, Yang YU. Prediction algorithm of close-orbit satellite based on orbit elements[J]. Optics and precision engineering, 2016, 24(10): 2540-2548. DOI： 10.3788/OPE.20162410.2540.

摘要

光电设备因太阳夹角变化、轨道遮挡等原因无法对卫星进行自动跟踪时，需要对卫星轨道进行预测。本文针对利用卫星轨道根数进行轨道预报时难以同时满足实时性和精度要求的问题，提出了一种新的基于轨道根数的卫星轨道预测方法。分析了卫星轨道的运行规律，根据低轨卫星的运行特点，利用椭圆曲线对卫星轨道进行预测，并对卫星轨道的轨道方程进行了近似处理。通过引入一些冗余变量简化了卫星轨道解算模型，在保证计算实时性的前提下，大大提高了轨道预测精度。实验显示：采用线性外推方法对卫星轨道进行预测时，预测5 s后，轨道预测的偏差会增大到10"，而采用本文提出的基于轨道根数的卫星轨道预测算法，预测50 s后的最大预测偏差均不超过2"，极大地提高了卫星轨道预测精度，实现了光电设备在无法对卫星进行自动跟踪时，能够对卫星进行“盲跟踪”。

Abstract

When a photoelectric device can not track the satellite due to the changed intersection angle of the sun or the orbit blocking

the satellite orbits have to be predicted. Because the traditional orbit prediction method based on orbit elements can not meet the requirements of real-time and precision measurement simultaneously

this paper proposes a new satellite orbit prediction method based on orbit elements. The movement rule of satellite orbits was analyzed

then the elliptic curves were used to predict the satellite orbits and to process approximately the orbit equation based on the characteristics of a low orbit satellite. Some redundancy variable quantities were induced to simplify the calculation model for satellite orbit

so that the orbit prediction accuracy is greatly increased in guaranteeing a good real-time calculation. The experiments show that when the linear extrapolation is used to predict the satellite orbit

its prediction deviation will increase to 10" after 5 s forecasting. However

if the method presented in this paper based on the orbit elements is used in the prediction

the maximum deviation is not more than 2" after 50 s prediction. The method has greatly promoted the prediction precision of satellite orbit

and makes the photoelectric device implement the ‘blind tracking’ for satellites when the automatic tracking is become to be invalid.

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