中低轨卫星高仰角时刻的轨道预测

崔爽; 郭立红; 王伟国; 李岩; 刘廷霞; 于国权

doi:10.3788/OPE.20152301.0245

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中低轨卫星高仰角时刻的轨道预测

信息科学 | 更新时间：2020-08-13

- 中低轨卫星高仰角时刻的轨道预测
- Orbit forecast of medium and low orbit satellite at the time of high elevation
- 光学精密工程 2015年23卷第1期页码：245-251
- 作者机构：
  
  1. 中国科学院长春光学精密机械与物理研究所,吉林长春,中国,130033
  2. 中国科学院大学北京,中国,100049
- 作者简介：
- 基金信息：
  
  中国科学院知识创新工程领域前沿资助项目()
- DOI：10.3788/OPE.20152301.0245
  中图分类号： V556
- 收稿日期：2013-12-06，
  
  修回日期：2014-01-29，
  
  纸质出版日期：2015-01-25
- 稿件说明：
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崔爽, 郭立红, 王伟国等. 中低轨卫星高仰角时刻的轨道预测[J]. 光学精密工程, 2015,23(1): 245-251

CUI Shuang, GUO Li-hong, WANG Wei-guo etc. Orbit forecast of medium and low orbit satellite at the time of high elevation[J]. Editorial Office of Optics and Precision Engineering, 2015,23(1): 245-251
崔爽, 郭立红, 王伟国等. 中低轨卫星高仰角时刻的轨道预测[J]. 光学精密工程, 2015,23(1): 245-251 DOI： 10.3788/OPE.20152301.0245.

CUI Shuang, GUO Li-hong, WANG Wei-guo etc. Orbit forecast of medium and low orbit satellite at the time of high elevation[J]. Editorial Office of Optics and Precision Engineering, 2015,23(1): 245-251 DOI： 10.3788/OPE.20152301.0245.

摘要

使用改进的拉普拉斯算法对人造卫星进行轨道预测时

在卫星仰角过高及卫星过顶点时刻其外推精度都较低

无法满足轨道预测的精度要求.本文基于对外推数据和实测数据的分析

提出了基于时间校正的轨道预测方法.该方法首先对外推数据和实测数据进行坐标旋转

然后用实测数据对外推数据进行时间校正

从而获得高精度的卫星轨道预测数据.利用水平式光电设备对卫星进行了跟踪实验.实验中使用了大于60 s时长的高精度自动跟踪数据

先进行运动方程的拟合

然后进行时间校正

外推出了超过20 s时长的高精度预测数据

且在卫星过顶点时刻

预测偏差可以保持在3"左右.实验结果表明

该方法有效地提高了卫星在高仰角时刻的轨道预测精度和保精度跟踪时间.

Abstract

When the improved Laplace algorithm is used to forecast the satellites' orbit

the extrapolate accuracy of the algorithm is usually relatively lower at a high elevation angle for the satellite

especially at the time of passing zenith. To meet the requirements of high-precision orbit forecast

this paper proposes a new orbit forecast method based on time-correction by analysis of extrapolating data and measured data. Firstly

the method performs a coordinate rotation for the extrapolating data and measured data

Then

it uses the measured data to correct extrapolation data on the time to obtain high-precision forecast data of satellite orbit. An experiment is carried out by using a horizontal photoelectric device with high-precision automatic tracking data more than 60 s length. By fitting the equations of motion and time correction

over 20 s duration precision forecast data are extrapolated

and the forecast error has be maintained at about 3" on the time of passing zenith. Experimental results show that this method effectively improves the orbit forecast accuracy and the time ensuring tracking accuracy when the satellite is at the time of high evelation angle.

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references

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