航天器离轨再入落点偏差分析  

Spacecraft De-orbit Reentry Footprint Bias Analysis

作　　者：童科伟[1] 邱亮 高朝辉[1] 唐庆博[1] 李扬[1] 焉宁[1] TONG Ke-wei;QIU Liang;GAO Zhao-hui;TANG Qing-bo;LI Yang;Yan Ning(China Academy of Launch Vehicle Technology Research& Development Center,Beijing 100076;China Academy of Space Technology,Beijing 100081,China)

机构地区：[1]中国运载火箭技术研究院研究发展中心,北京100076 [2]中国空间技术研究院,北京100081

出　　处：《空间碎片研究》2018年第1期20-25,共6页Space Debris Research

摘　　要：大型航天器、火箭末级、上面级寿命末期离轨再入时无法在大气层内完全烧毁,因此需要精确计算航天器、火箭末级、上面级再入预报与落点散布问题。基于高精度轨道预报模型设计了一种能够考虑轨道摄动的高精度轨道/再入弹道计算分析方法,可考虑地球非球形引力摄动、日月三体摄动、光压及大气阻力,与商业软件STK相比,计算结果一致。同时设计了一种基于蒙特卡罗仿真技术的再入弹道落点偏差计算软件,能够计算航天器、火箭末级、上面级再入落点散布。本文的分析方法可应用于在轨安全领域,对人类生命财产安全防护具有重要意义。Large scale spacecraft, rocket final stage and upper stage cannot be burned out during reentry atmosphere when finished their mission.It is necessary to calculate the footprint distribution of spacecraft, rocket final stage and upper stage.An orbit/reentry trajectory calculation analysis program is designed based on high precision orbit propagation model which can consider earth nonspherical gravity, luni-solar third body perturbation, solar pressure and atmospheric drag.Compared with STK, it can get the same result.Based on standard orbit propagation program, an reentry trajectory footprint bias software using Monte Carlo simulation technology is designed, which can be used for calculating the footprint distribution of spacecraft, rocket final stage and upper stage.The approach can be used for on-orbit safety field, and can be used for human property protection against space debris.

关 键 词：离轨 再入 落点 偏差 

分 类 号：V421.1[航空宇航科学与技术—飞行器设计]