双月旁转向轨道的修正方法研究  

CORRECTION METHODS ANALYSIS OF DOUBLE LUNAR-SWINGBY TRAJECTORY

作　　者：罗宗富[1] 孟云鹤[1] 汤国建[1] 

机构地区：[1]国防科技大学航天与材料工程学院,长沙410073

出　　处：《力学学报》2011年第2期408-416,共9页Chinese Journal of Theoretical and Applied Mechanics

基　　金：国家自然科学基金(10702078);国防科技大学校预研基金(JC08-01-05);国防科技大学优秀研究生创新(B100101)资助项目;湖南省研究生科研刨新项目~~

摘　　要：双月旁转向轨道是深空探测中有应用潜力的一类非线性轨道.在CR3BP模型下得到了双月旁转向轨道,通过分析轨道的误差传播特性,制定了双月旁转向轨道的修正原则,提出了"关键节点"加"显式制导"的修正思路;给出了考虑太阳引力作用的R4BP模型,针对初始误差、导航误差、修正执行误差和太阳引力摄动偏差进行了轨道修正仿真,得到了基于Monte-Carlo方法的轨道修正统计结果.在此基础上,采用了"初值速度补偿"与"显式制导"相结合的思路修正初始误差、导航误差、修正执行误差和太阳引力作用,仿真表明:这一方法能够较大程度地降低轨道修正所需的冲量.结果和结论能够为双月旁转向轨道的工程应用提供参考.Double Lunar-Swingby（DLS） trajectory is a type of non-linear orbit which has potential applications in the deep-space exploration.A nominal trajectory is given under CR3BP model,and its dynamic characteristic is analyzed.According to the error dispersion of the nominal trajectory,several correction principles are established.Considering the solar gravitational perturbation,the R4BP model is established.A method of explicit guidance at the＂key node＂is developed,and the correction maneuver results of the initial error, navigation error,maneuver error and the solar gravitational perturbation are obtained.The statistical dispersion analysis is carried out with Monte-Carlo simulation.Based on these works,a new method of initial velocity supplement combined with explicit guidance is proposed to correct the initial error,navigation error,maneuver error and the solar gravitational influence,and the parameters including the magnitude of supplement velocity and time of TCM are optimized.The simulation results show that this method can reduce the correction maneuver obviously.The results and conclusions of this paper can provide a reference for the engineering applications of DLS trajectory.

关 键 词：双月旁转向 轨道修正 限制性三体问题 太阳引力摄动 显式制导 初值补偿 Monte-Carlo 

分 类 号：V412[航空宇航科学与技术—航空宇航推进理论与工程]