基于双星定位系统的近地卫星定轨精度仿真  

Research on LEO Orbit Determination Precision Simulation Based on Bi-satellite Positioning System

作　　者：赵德勇[1] 潘晓刚[1] 王炯琦[1] 周海银[1] 王正明[1] 

机构地区：[1]国防科技大学数学与系统科学系,长沙410073

出　　处：《系统仿真学报》2006年第6期1437-1441,共5页Journal of System Simulation

基　　金：全国优秀博士论文作者专项基金(200140)

摘　　要：通过对测距误差特性的统计分析,建立了用于近地卫星精密定轨的距离和观测数据仿真方法,在此基础上构建了基于卫星动力学方程的精密定轨模型,设计了一种基于数值融合法的精密定轨改进算法和测距系统误差参数估计算法,并进行了六类仿真实验。仿真计算结果表明,基于一天的距离和观测数据仿真计算得到的近地卫星定轨精度可以达到15.98米,与利用其他精密定轨软件系统在相同仿真条件下得到的近地卫星定轨精度基本相当,但该算法避免求解状态转移矩阵,具有计算速度快,稳健性好等特点。A basic method of range sum observation data simulation for Low Earth Orbiter （LEO） precise orbit determination （POD） was constructed by statistical analysis of ranging error characteristic, and a precise orbit determination model was established based on satellite dynamics equation. On the above model, an improved precise orbit determination algorithm was designed based on numerical fusion algorithm and ranging system error parameters estimation algorithm, and six kinds of simulation experiments were carried out. Simulation computation results show that LEO orbit determination precision can achieve 15.98 meters which is estimated by one day range sum simulation data, and under the same simulation conditions, it is equivalent to that of other precise orbit determination software system. But the algorithm avoids solving LEO state transition matrix, and has the characteristic of faster computation velocity and higher stability.

关 键 词：精密定轨 测距误差仿真 数值融合算法 系统误差参数估计 

分 类 号：TP391[自动化与计算机技术—计算机应用技术]