基于龙格库塔法的GLONASS轨道仿真研究  

RESEARCH ON GLONASS ORBIT SIMULATION BASED ON RUNGE-KUTTA METHOD

作　　者：卢祥[1,2] 袁运彬 蒋振伟[1,2] 

机构地区：[1]大地测量与地球动力学国家重点实验室,武汉430077 [2]中国科学院大学,北京100049

出　　处：《大地测量与地球动力学》2014年第3期137-141,共5页Journal of Geodesy and Geodynamics

基　　金：国家自然科学基金重点项目(41231064);国家863计划项目(2012AA121803)

摘　　要：将龙格库塔法引入GLONASS轨道仿真,研究步长参数设置对结果的影响,定量分析仿真结果与广播星历的差异和算法效率,并进行长时间仿真试验分析。结果表明,步长参数设置为1-300 s时能兼顾算法效率与结果精度;仿真结果与广播星历的差异随时间延长而增大,仿真300 min时X、Y、Z方向差异分别为266.43、246.13、336.06 m,每仿真一个历元24颗星数据耗时约2 ms。龙格库塔法适用于GLONASS轨道仿真。Runge-Kutta method was introduced to GLONASS orbit simulation to analyze how the step length parameter effects on simulated results, the efficiency of Runge-Kutta method and the difference between simulated results and broadcast orbit. The result shows that step the balance between algorithm efficiency and accuracy can be keeped though setting step length as 1 s -300 s. The difference between simulated results and broadcast ephemeris increases with time, and reaches about 250m in X, Y,Z directions for 300 minutes simulation time duration. It takes 2 ms to simulate 1 epoch 24 satellites orbit data. According the research, Runge-Kutta method can be used for GLONASS orbit simulation.

关 键 词：龙格库塔法 GLONASS 轨道仿真 积分步长 积分时长 

分 类 号：P228[天文地球—大地测量学与测量工程]