中国空间科学技术

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卫星初始轨道确定方法研究

祝转民;徐宗本;   

  1. 西安交通大学理学院,西安交通大学理学院 西安710049,西安710049
  • 发布日期:2007-06-25

Study of Satellite Initial Orbit Determination Method

Zhu Zhuanmin Xu Zongben(Mathematical College of Xi′an Jiaotong University,Xi′an 710049)   

  • Online:2007-06-25
  • Supported by:
    国家博士后科学基金资助项目(20040350685)

被引次数

14

摘要： 卫星精密轨道确定过程实际上是通过求解轨道动力学微分方程组而对初始轨道不断改进的过程,因此,轨道确定的精度与速度不但依赖于求解微分方程组的具体算法,同样依赖于初始轨道的精度与准确性。针对多站测距/距离和数据,建立了一种轨道初值计算的几何方法,该方法集折射误差修正方法于一体,在进行观测数据折射误差修正的基础上,可以得到卫星在任意时刻的轨道初值。

关键词: 精密定轨, 多站测距, 初轨确定, 卫星轨道, 仿真

Abstract: Actually,the satellite precision orbit determination is a iterated process to improve the initial orbit by solving the dynamic differential equation group.So that,the precision and calculating rate of the orbit is depends on the solve algorithm of the differential equation and the precision and veracity of the initial orbit.For the ranges or two-way ranges data observed by some stations synchronously,a geometry method was proposed to determine the satellite initial orbit.The method combined the radio wave refraction error correction method with itself can improved the precision greatly.