一种利用卫星星历计算机动加速度的方法  

A Method to Calculate the Short-Time Orbit Maneuver Acceleration Based on the Satellite Ephemeris

作　　者：崔双星 杨志涛[2] 刘卫 王荣兰 向开恒 贺泉 吴中灏 CUI Shuang-xing;YANG Zhi-tao;LIU wei;WANG Rong-lan;XIANG Kai-heng;HE Quan;WU Zhong-hao(China Satellite Network Group Co.,Ltd,Beijing 100029,China;National Astronomical Observatories,Chinese Academy of Sciences,Beijing 100012,China;National Space Science Center,Chinese Academy of Sciences,Beijing 100190,China)

机构地区：[1]中国星网网络创新研究院,北京100029 [2]中国科学院国家天文台,北京100012 [3]中国科学院国家空间科学中心,北京100190

出　　处：《空间碎片研究》2023年第3期19-28,共10页Space Debris Research

摘　　要：对于近地轨道卫星,由于受大气影响较大,轨道机动比较频繁,…轨道机动的快速检测以及推力的计算,对保障空间目标运行安全及故障分析意义重大。本文基于公开发布的卫星星历数据,提出了基于卫星星历识别轨道机动的方法,并通过轨道预报迭代反演和能量转化两种方式,实现了小推力条件下卫星轨道机动加速度的计算,两种计算方法计算结果有很好的一致性。应用该方法基于星历文件对多个星座目标进行机动识别与加速度解算,以解算结果对卫星轨道进行星历仿真,仿真结果与发布的星历基本一致。For LEO(Low Earth Orbit)satellites,due to the greater impact of the atmosphere,orbital maneuvers are frequent.The rapid detection of orbital maneuvers and the calculation of thrust are of great significance for ensuring the operational safety and fault analysis of space targets.Based on the publicly released satellite ephemeris data,a method of identifying satellite orbit maneuver based on the satellite ephemeris is proposed.Through orbit prediction inversion and energy conversion,the calculation of satellite orbit maneuver acceleration under low thrust conditions is realized.The calculation results of the two methods are very consistent.By adding this maneuver acceleration to simulate the satellite orbit,the simulation results are basically consistent with the published ephemeris.

关 键 词：轨道机动 小推力 轨道机动识别 定轨 

分 类 号：V524[航空宇航科学与技术—人机与环境工程]