利用HPOP轨道仿真模型实现接收机自主历书外推  

Executing Receiver Autonomous Ephemeris Extrapolation by HPOP Model

作　　者：车通宇 杨力[1] 张传定 闫志闯[1] 王琰[1] 

机构地区：[1]信息工程大学,河南郑州450001 [2]北京卫星导航中心,北京100094

出　　处：《全球定位系统》2015年第4期18-22,共5页Gnss World of China

基　　金：国家自然科学基金(批准号:41174026)

摘　　要：提出了一种利用轨道仿真的思路实现接收机自主历书外推的方法。为了实现对GPS等导航卫星的高精度轨道仿真,需要知道卫星相关的物理参数,但实际中由于保密等条件限制很多参数无法获得。本文通过HPOP高精度轨道外推模型,利用控制变量的思路,基于已知先验信息的统计经验值,通过配置物理参数变量来外推卫星轨道,将其同IGS精密轨道比较,以分析得出最优的参数组合。分析表明:设置卫星质量为975kg,太阳能帆板反射系数为1.0,面质比为0.02005,可以实现对于GPS卫星的高精度轨道仿真;其外推多日的精度满足仿真应用需要;该方法可以用于接收机自主历书外推。The article presents a method to execute Receiver Autonomous Ephemeris Extrapolation by orbit simulation.It needs to know the physical related parameters of the satellites to execute high-precision orbit simulation for GPS and other navigation satellites.But in practice many parameters can＇t be received due to confidentiality restrictions or other conditions.It executed Receiver Autonomous Ephemeris Extrapolation by HPOP model with the method that configured the physical related parameters and compared the extrapolated orbit with IGS ephemeris.The analysis shows：It can execute high-precision orbit simulation by setting the physical related parameters with the mass of 975 KG,solar panel reflection coefficient of 1.0,M/A coefficient of 0.02005;The RMS of the extrapolation reaches the needs of orbit simulation.The method can be used in Receiver Autonomous Ephemeris Extrapolation.

关 键 词：HPOP模型 GPS卫星 轨道仿真 历书外推 

分 类 号：P228.4[天文地球—大地测量学与测量工程]