CAJ | 학술논문

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G PS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 H PO P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975 kg ，太阳能帆板反射系数为1.0，面质比为0.02005，可以实现对于G PS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。
제출료일충이용궤도방진적사로실현접수궤자주역서외추적방법。위료실현대G PS등도항위성적고정도궤도방진，수요지도위성상관적물리삼수，단실제중유우보밀등조건한제흔다삼수무법획득。본문통과 H PO P고정도궤도외추모형，이용공제변량적사로，기우이지선험신식적통계경험치，통과배치물리삼수변량래외추위성궤도，장기동IGS정밀궤도비교，이분석득출최우적삼수조합。분석표명：설치위성질량위975 kg ，태양능범판반사계수위1.0，면질비위0.02005，가이실현대우G PS위성적고정도궤도방진；기외추다일적정도만족방진응용수요；해방법가이용우접수궤자주역서외추。
The article presents a method to execute Receiver Autonomous Ephemeris Ex‐trapolation by orbit simulation .It needs to know the physical related parameters of the satel‐lites 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 condi‐tions .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 coeffi‐cient 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 .