中国空间科学技术

中国空间科学技术

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SGP4/SDP4模型用于空间碎片轨道预测的精度分析

韩蕾,陈磊,周伯昭   

  1. 国防科学技术大学,国防科学技术大学,国防科学技术大学 长沙410073 ,长沙410073 ,长沙410073
  • 发布日期:2004-08-25

Precision Analysis of SGP4/SDP4 Implemented in Space Debris Orbit Prediction

Han Lei Chen Lei Zhou Bozhao(National University of Defense Technology, Changsha 410073)   

  • Online:2004-08-25

被引次数

136

摘要： 为保证航天任务的顺利完成 ,必须采用一定的模型 ,对可能威胁目标轨道的空间碎片进行跟踪预测。文中首先给出标称轨道的计算模型 ;接着介绍两行轨道根数 (TLE)和考虑了简化常规 /深空扰动的近似解析解模型 (SGP4/SDP4) ,并提供TLE使用的坐标系和惯性系之间的转换 ;然后以典型轨道为例 ,分析SGP4/SDP4与标称轨道的偏差。运算结果表明SGP4/SDP4运算速度快 ,满足一定精度 ,可以用于空间碎片的轨道预测和初步威胁评估。

关键词: 空间碎片, 轨道分析, 精度分析, 预测

Abstract: To insure the security of space mission, the dangerous big debris must be tracked and predicted. Firstly, the computing model of standard orbit is given in this paper. Secondly the coordinate transformation from True Equator and Mean Equinox of Date to Earth Mean Equator and Equinox of Date which two-line mean element (TLE)used is provided. And Simplified General Perturbations Version 4 and Simplified Deep-space Perturbation (SGP4/SDP4)which developed from analytic orbital theory are introduced. Then according to the typical orbits, the precision of SGP4/SDP4 is analyzed. The result shows that SGP4/SDP4 are efficient and valid to the initial prediction of danger.