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.
出处
《大地测量与地球动力学》
CSCD
北大核心
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)
