一种深空天文测角导航中的星历误差抑制方法  

A Method Against Ephemeris Error in Deep Space Celestial Angle Measurement Navigation

作　　者：宁晓琳[1] 晁雯 杨雨青[1] NING Xiao-lin;CHAO Wen;YANG Yu-qing(School of Instrumentation and Optoelectronic Engineering,Beihang University,Beijing 100191,China)

机构地区：[1]北京航空航天大学仪器科学与光电工程学院

出　　处：《宇航学报》2019年第12期1412-1421,共10页Journal of Astronautics

基　　金：国家自然科学基金(61503013,61722301)

摘　　要：以火星探测器为例,提出一种以星光角距/时间差分星光角距作为量测量的星历误差抑制方法,分析了火卫一星历误差对导航精度的影响,建立了火卫一时间差分星光角距的量测模型。通过将火星星光角距和火卫一星光角距相结合,发挥了两种量测的优势,实现了对火卫一星历误差的抑制。仿真结果表明,基于星光角距/时间差分星光角距天文导航方法的位置误差是传统基于星光角距天文导航方法的64%,是基于时间差分星光角距导航方法的58%。此外,还分析了导航恒星个数、火星敏感器精度、火卫一敏感器精度、星历误差大小和滤波周期对导航性能的影响。Taking a Mars explorer as an example,a method using the starlight angle/time differential starlight angle against ephemeris error is proposed,the influence of the Phobos ephemeris error on navigation accuracy is analyzed,the time differential starlight angle measurement model of Phobos is established,and it is measured together with the starlight angle of Mars to eliminate the Phobos ephemeris error.The simulation results show that the position error using the starlight angle/time differential starlight angle method is 64% of that of the traditional method and 58% of that of the time differential method.In addition,the influence of the number of navigation stars,the accuracy of the Mars sensor and Phobos sensor,the magnitude of the ephemeris error as well as the filter period are analyzed.

关 键 词：深空探测器 天文测角导航 星历误差 时间差分 

分 类 号：V448.21[航空宇航科学与技术—飞行器设计]