摘要
嫦娥四号探测器预选着陆点在月球背面冯·卡门撞击坑,着陆区域较小,且要求定时定点着陆控制,同时着陆前的飞行时间长、阶段控制多,因而精确控制难度较大.针对该问题,基于轨道偏差随摄动的演化特性,结合解析法和数值法优点,提出了动力学控制参数的半解析求解方法.首先,通过对着月点和动力下降点位置的分析,得到了着月点和动力下降点位置的解析关系.同时,分析得到了着陆点经度偏差与轨道平面偏差的解析关系.其次,研究了轨道控制策略,按飞行阶段给出了轨道平面偏差到偏航角的转换方法和着月时间到目标半长轴的调整方法.最后,给出了本方法在嫦娥四号工程中的实际应用情况,基于对实际任务结果的分析可见,实现了着月控制参数的快速精确求解.
The pre-selected landing point of Chang’E-4 probe lies in von Karman Crater on the farside of the Moon.Because the available landing zone is very small,the probe needs several orbit maneuvers for pinpoint and punctual landing.In view of this problem,a method base on analytic solution and simple iteration is put forward.Firstly,the relationship between landing point and the lunardescent-phase initial point is analyzed,and corresponding conversion formula is given.Secondly,the relationship between longitude deviation of landing point and deviation of orbit plane is analyzed.Thirdly,a set of proper orbit control strategies of the probe are proposed and discussed,including translation methods from deviation of orbit plane to yaw angle of maneuver and adaptation methods from landing time to semi-major axis according to different flying phases.Finally,the application of the proposed strategies and algorithms of orbit control in Chang’E-4 mission is introduced,and the feasibility and validity are illustrated by the actual results.
作者
刘勇
李革非
郝大功
马传令
LIU Yong;LI GeFei;HAO DaGong;MA ChuanLing(Beijing Aerospace Flight Control Center,Beijing 100094,China;Aerospace Flight Dynamics Laboratory,Beijing 100094,China)
出处
《中国科学：技术科学》
EI
CSCD
北大核心
2019年第11期1268-1274,共7页
Scientia Sinica(Technologica)
基金
国家自然科学基金(批准号:11773004,61573049)
探月工程重大专项资助项目
关键词
嫦娥四号
定时定点着月
轨道控制
轨道平面修正
近月制动
环月降轨
Chang’E-4
pinpoint
and
punctual
landing
orbit
maneuver
orbital
plane
adjustment
braking
at
perilune
lunar
descent
