【作者】 周芳；

【导师】 张汉清；

【作者基本信息】 南京航空航天大学 ， 导航、制导与控制， 2019， 硕士

【摘要】 “探月工程”作为我国深空探测领域的重大专项,在实施过程中需要满足不同的技术需求。在探月任务的全过程中,精确导航定位技术是探月工程顺利实施的关键技术之一。本文针对探月导航方案的设计主要包含三个方面的内容:首先,密切结合探月任务实施过程中的空间动力学特性及月面环境特征,详细研究地月空间圆形限制性三体问题的动力学模型,基于拉格朗日点独特的动力学特性,利用构造流函数法求解周期轨道,利用庞加莱截面法求解地月系统的拟周期轨道,在圆型限制性三体问题基础上重点设计一种能够对共线拉格朗日点全类型周期、拟周期轨道进行系统计算的逃逸时间函数法,并探索拉格朗日点新型轨道的基本性质,完整拓展导航星座轨道的设计空间;其次,在拉格朗日点轨道计算的基础上,进行导航星座的构型设计,研究导航星座的自主定轨流程,分析导航星座的自主定轨误差与几何精度因子,形成多种基于拉格朗日点轨道的导航星座备用设计方案;最后,为弥补导航星座方法可能存在的覆盖盲区问题,研究基于扩展卡尔曼滤波与信标网络的月面导航方法,整合提出基于信标网络的视觉导航辅助方案,并分析基于自然信标定位与基于人造信标定位的精度问题;最终以“基于拉格朗日点导航星座的探月导航方案”为主,“基于信标网络的月面视觉导航方案”为辅的探月导航方案。本文相关研究成果能够对我国探月工程方案实施提供可行的备选导航方案以及相关的技术支持。更多还原

【Abstract】 As a major project in the field of deep space exploration in China,the lunar exploration project needs to meet different technical needs in the implementation process.In the whole process of lunar exploration mission,precise navigation and positioning technology is one of the key technologies for the smooth implementation of lunar exploration project.In this paper,the design of lunar exploration navigation scheme mainly includes three aspects:Firstly,the dynamic model of three-body problem with circular restriction in lunar space is studied in detail based on the space dynamics characteristics and lunar environment characteristics of lunar exploration mission.Based on the unique dynamic characteristics of Lagrange point,the periodic orbit is solved by constructed flow function method,the quasi-periodic orbit of lunar system is solved by Poincare section method,and the three-body problem with circular restriction is solved by Poincare section method.On the basis of the problem,a method of escape time function which can calculate the periodic and quasi-periodic orbits of collinear Lagrange points systematically is designed.The basic properties of the new orbit of Lagrange points are explored and the design space of navigation constellation orbits is fully expanded.Secondly,on the basis of Lagrange point orbit calculation,the configuration design of navigation constellation is carried out,the autonomous orbit determination process of navigation constellation is studied,and the autonomous orbit determination error and geometric accuracy factors of navigation constellation are analyzed,and various alternative design schemes of navigation constellation based on Lagrange point orbit are formed.Finally,in order to remedy the problem of blind area covered by navigation constellation method,the lunar navigation method based on extended Kalman filter and beacon network is studied,and a visual navigation aided scheme based on beacon network is proposed,and the accuracy of natural beacon positioning and artificial beacon positioning is analyzed.Finally,the lunar navigation scheme based on Lagrange point navigation constellation is proposed.” Mainly,the lunar visual navigation scheme based on beacon network is supplemented by the lunar exploration navigation scheme.The research results in this paper can provide feasible alternative navigation schemes and related technical support for the implementation of China’s lunar exploration project.更多还原