利用Halo轨道仿真开展嫦娥四号中继星与月面设备干涉基线的研究  

Research of Interferometry Baselines Between CE-4 Rover and Lunar Facility Using Halo Orbit Simulation

作　　者：武宇翔 温卫斌[1,2] 平劲松 朱新颖[1,2] 张洪波 孔德庆[1,2,3] 戴舜 薛喜平[1,2] 李臣 Wu Yuxiang;Wen Weibin;Ping Jinsong;Zhu Xinying;Zhang Hongbo;Kong Deqing;Dai Shun;Xue Xiping;Li Chen(National Astronomical Observatories,Chinese Academy of Sciences,Beijing 100101,China;Key Laboratory of Lunar and Deep Space Exploration,Chinese Academy of Sciences,Beijing 100101,China;University of Chinese Academy of Sciences,Beijing 100049,China)

机构地区：[1]中国科学院国家天文台,北京100101 [2]中国科学院月球与深空探测重点实验室,北京100101 [3]中国科学院大学,北京100049

出　　处：《天文研究与技术》2021年第1期69-76,共8页Astronomical Research & Technology

基　　金：国家自然科学基金(11941002,11941003);中国科学院-荷兰科学组织射电天文国际合作项目(GJHZ1867)资助.

摘　　要：初步建立了嫦娥四号中继星的晕轨道(Halo轨道)数值模型,将其应用于空间低频射电天文观测的干涉测量仿真,以地月拉格朗日平动点L 2区域的Halo轨道为基础,以发布的嫦娥四号中继星理论轨道为参考,校准和调整模型参数,通过时间和空间参考系统的变换,把轨道数据转换到L 2点旋转坐标系。然后对比Halo轨道模型与理论轨道数据之间的差别,对比模拟和理论数据分别与月面设备形成基线的长度,并对结果进行分析。两者在所分析的运行阶段,与月面设备联成基线的长度差在60 km以内,在高频频带基本满足干涉测量条纹搜索对基线初值精度的需求。An orbit model for Chang′E-4 relay satellite is established which is supposed to be used in a simulation of space low-frequency radio interferometry.Based on classic Lagrange libration point L 2 Halo orbit,some parameters are calibrated and modified by the theoretical orbit of Chang′E-4 relay satellite,converting theoretical orbit to a rotation orbit in the vicinity of L 2 point through time and coordinate reference transferring.Comparisons between the Halo orbit model and the theoretical orbit model are carried out,according to which,their baselines to lunar-surface facility are calculated respectively and analyzed.In the analysis,differences between the baselines are below 60 km,which satisfy the needs of interferometry fringe searching in the HF band.

关 键 词：HALO轨道 平动点 参考系 仿真 

分 类 号：P171.4[天文地球—天文学]