Onboard Lunar Orbit Determination Using One-Way Uplink Doppler data

This dataset supports the study “Onboard Lunar Orbit Determination Using One-Way Uplink Doppler: Effects of Orbit Geometry and Receiver-Clock Stability under Force-Model Mismatch.” It contains the processed simulation data used to reproduce all nine figures and ten tables in the manuscript. The data were generated from Monte Carlo simulations of a spacecraft in low lunar orbit tracked intermittently by three Chinese Deep Space Network stations using one-way uplink Doppler. Doppler measurements were processed onboard using an eight-state square-root unscented Kalman filter that estimated spacecraft position, velocity, receiver-clock drift, and the solar-radiation-pressure coefficient. The simulations examined four orbit geometries, three receiver-clock stability levels, station-frequency residuals, and station time-tag residuals under a reduced onboard force model. Files beginning with figure_ contain the numerical data underlying the correspondingly numbered manuscript figures. These include force-acceleration histories, time-dependent median and 90th-percentile position errors, and per-realization comparisons between empirical position error and formal filter uncertainty. Files beginning with table_ contain the scenario definition, test matrix, accuracy statistics, and filter-consistency statistics reported in the correspondingly numbered manuscript tables. All Monte Carlo cases contain 108 realizations. Column names specify the represented quantity and its unit. Position and velocity accuracy statistics are evaluated over the final 24 hours of each three-day simulation unless otherwise stated. The data show that one-way uplink Doppler can support onboard lunar orbit determination, although performance depends on orbit geometry, receiver-clock stability, ground-reference errors, force-model uncertainty, and the observability of estimated force parameters.本数据集支撑研究论文《采用单向上行链路多普勒（one-way uplink Doppler）的在轨月球定轨：力模型失配条件下轨道几何与接收机时钟稳定性的影响》，包含用于复现该论文全部9幅插图与10张表格的经处理的仿真数据。 该数据源于蒙特卡洛仿真（Monte Carlo simulations），仿真对象为处于月球低轨的航天器，由3个中国深空测控站（Chinese Deep Space Network）采用单向上行链路多普勒方式进行间歇式跟踪。多普勒测量数据在轨通过八状态平方根无迹卡尔曼滤波器（square-root unscented Kalman filter）进行处理，该滤波器可估计航天器位置、速度、接收机时钟漂移以及太阳辐射压力系数（solar-radiation-pressure coefficient）。本次仿真在简化的在轨力模型条件下，考察了4种轨道几何构型、3种接收机时钟稳定性等级、站址频率残差以及站址时标残差对定轨性能的影响。 以figure_开头的文件，包含与论文中对应编号插图配套的数值基础数据，包括力加速度历史曲线、随时间变化的位置误差中位数与90分位数，以及各次仿真实现中经验位置误差与滤波器形式化不确定性的逐次对比结果。以table_开头的文件，包含对应编号论文表格中给出的场景定义、测试矩阵、精度统计量以及滤波器一致性统计量。 所有蒙特卡洛仿真案例均包含108次仿真实现。列名指定了所表征的物理量及其单位。除非另有说明，位置与速度精度统计量均基于单次3天仿真的最后24小时进行计算。实验结果表明，尽管定轨性能依赖于轨道几何构型、接收机时钟稳定性、地面参考误差、力模型不确定性以及待估计力参数的可观测性，单向上行链路多普勒仍可支撑在轨月球定轨任务。