摘要
采用一种变相的"非差"动力定轨方法,建立了相应的数学模型,编制了星载GPS低轨卫星的定轨软件,并以此分析了定轨过程中各主要误差源对定轨的影响以及所能达到的定轨精度和预报精度。该方法以相位平滑伪距为观测值,通过对同一历元的观测值进行卫星间求差,消除了星载GPS接收机钟差,模型简单,求解参数少。在只估计初始坐标和速度参数、考虑各种误差的综合影响时,定轨一天的径向精度约为3m,能满足一定的定轨精度要求。
An alternative zero-difference orbit determination approach is used to establish the corresponding mathematic model and develop the orbit determination software of low earth orbit satellite with satellite-based GPS. and effects of main error sources on orbit determination are studied. Also orbit determination and prediction precision attained with this method are studied deeply. Simulated calculation reveals that this method can be used in precise orbit determination.
出处
《山东科技大学学报（自然科学版）》
CAS
2004年第4期12-15,共4页
Journal of Shandong University of Science and Technology(Natural Science)
基金
国家自然科学基金资助项目(40204001)
中科院知识创新工程领域前沿项目(030185)
关键词
非差定轨
相位平滑伪距
误差分析
轨道预报
zero-difference orbit determination
phase smoothing pseudorange
error analysis
orbit prediction
