用地球GNSS实现月球卫星高精度轨道与钟差估计
GNSS-based Lunar Orbit and Clock Estimation With Stochastic Cloning UD Filter
- 基于随机克隆UD分解滤波器处理低可观测条件下的精密载波相位数据
- 实现米级轨道精度和亚毫米/秒级速度精度，满足未来月球导航要求
- 适合从事深空导航、月球轨道系统设计的研究人员参考
本文提出一种基于地球全球导航卫星系统（GNSS）的月球导航卫星轨道与钟差估计框架。为应对月球距离下观测性差的问题，提出一种随机克隆UD因子化滤波器与延迟状态平滑器，显著提升处理高精度时间差分载波相位（TDCP）测量时的数值稳定性。建立了完整的动力学与测量模型，显式考虑轨道与钟差状态间的相对论耦合、月球时间尺度转换及电离层、等离子体层和Shapiro延迟效应。通过高保真蒙特卡洛仿真验证，综合无电离层伪距与TDCP测量可实现米级轨道精度和亚毫米/秒级速度精度，满足未来月球增强导航服务（LANS）对星上信号误差的严苛要求。
原文摘要 · Abstract (English)
This paper presents a terrestrial GNSS-based orbit and clock estimation framework for lunar navigation satellites. To enable high-precision estimation under the low-observability conditions encountered at lunar distances, we develop a stochastic-cloning UD-factorized filter and delayed-state smoother that provide enhanced numerical stability when processing precise time-differenced carrier phase (TDCP) measurements. A comprehensive dynamics and measurement model is formulated, explicitly accounting for relativistic coupling between orbital and clock states, lunar time-scale transformations, and signal propagation delays including ionospheric, plasmaspheric, and Shapiro effects. The proposed approach is evaluated using high-fidelity Monte-Carlo simulations incorporating realistic multi-constellation GNSS geometry, broadcast ephemeris errors, lunar satellite dynamics, and ionospheric and plasmaspheric delay computed from empirical electron density models. Simulation results demonstrate that combining ionosphere-free pseudorange and TDCP measurements achieves meter-level orbit accuracy and sub-millimeter-per-second velocity accuracy, satisfying the stringent signal-in-space error requirements of future Lunar Augmented Navigation Services (LANS).
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