新型运载火箭空间碎片减缓研究  

Research on Space Debris Mitigation of New Launch Vehicle

作　　者：周遇仁 杨帆 刘昶 李云飞 张晓东 

机构地区：[1]上海宇航系统工程研究所,上海201109

出　　处：《上海航天》2016年第B05期8-12,共5页Aerospace Shanghai

摘　　要：对新型运载火箭空间碎片减缓方式进行了研究,采用主动离轨及剩余推进剂排放结合的模式以满足要求。针对长征六号(CZ-6)新一代运载火箭三子级的特点,采用俯仰偏航姿控发动机连续正推和贮箱内剩余推进剂排放提供离轨动力,给出了主动离轨的基本原理及剩余推进剂真空排放推力的工程计算方法,设计了离轨时序,建立了末级在轨时间计算模型,预估得到了末级在轨时间。飞行试验结果表明:火箭末级离轨效果明显,缩短了末级在轨时间,且有效排空了贮箱内剩余推进剂。In order to accomplish space debris mitigation of the new generation launch vehicle,active deorbit and residual propellant discharge were usually used.According to the character of the third stage of CZ-6launch vehicle,a method using attitude engine and residual propellant discharging to provide the energy of deorbit was presented.The effective and reliable propellant discharging vacuum force calculation method and on orbit time calculation model were used to estimate the time on orbit（less than 10years）of the upper stage.The results of flight experiment showed the measure was feasible and effective.

关 键 词：空间碎片 末级 减缓 主动离轨 姿控发动机 在轨时间 剩余推进剂 排放 

分 类 号：V528[航空宇航科学与技术—人机与环境工程]