日晕轨道卫星的转移轨道中途修正研究  

On Midcourse Correction of Transfer Trajectory for Halo Orbiters

作　　者：胡少春[1,2] 孙承启[1,2] 刘一武[1,2] 

机构地区：[1]北京控制工程研究所,北京100190 [2]空间智能控制技术重点实验室,北京100190

出　　处：《空间控制技术与应用》2012年第5期21-26,共6页Aerospace Control and Application

摘　　要：由于平动点任务探测器对各种误差源和摄动因素的敏感性,因此必须考虑转移轨道的中途修正问题.以晕轨道近地点入轨的转移轨道为例,进行了初始发射误差的灵敏度分析,提出了三脉冲和四脉冲两种中途修正方案,并且讨论了转移轨道初始误差、导航误差、机动执行误差等误差源和地球摄动、月球摄动、太阳光压摄动等摄动因素对转移轨道修正代价和修正效果的影响.仿真得到了修正时刻和误差量与修正量之间的关系,Monte Carlo仿真结果表明给出的两种修正方案是可行的.The transfer trajectory of libration point mission varies considerably due to the high sensitivity of error sources and perturbation forces.So,the midcourse correction of transfer trajectory must be considered.For the Halo perigee insertion transfer trajectory,the sensitivity to initial launch errors is firstly analyzed in this paper,and two correction schemes of three impulses and four impulses are put forward.And then the influence of the factors such as initial errors,navigation errors,maneuver performance errors,and earth gravitational perturbation,moon gravitational perturbation,and sunlight pressure perturbation on transfer trajectory correction cost and effect is discussed.The relation between correction times and maneuvers and the relation between errors and maneuvers are achieved by numerical simulation.The Monte Carlo simulation results show the feasibility of proposed two schemes.

关 键 词：晕轨道 中途修正 误差源 摄动因素 MONTE Carlo仿真 

分 类 号：V412.41[航空宇航科学与技术—航空宇航推进理论与工程]