基于日地平衡点的小行星捕获轨道设计与优化

发布时间：2019-01-05 21:26

【摘要】：小行星因含有太阳系形成初期残留的物质和太阳系演化形成过程中的丰富信息而备受关注。将小行星捕获至地球附近,不但有助于获得小行星含有原始信息的物质,而且有利于小行星丰富资源的开发和利用。本文以小行星捕获为背景,研究了基于日地平衡点的小行星捕获轨道设计与优化问题,主要内容如下:在捕获目标星的选择方面,本文从轨道特征、光谱类型和尺寸分布等方面对近地小行星的物理特征和轨道特性进行了比较全面的分析,从而给出了捕获目标星的选择条件,并结合能量需求筛选出适合捕获任务的备选目标星。基于脉冲转移方式,本文采用两脉冲和多脉冲转移,并结合三体轨道动力学系统流形理论、弱稳定边界理论以及月球借力理论,分别给出了将目标小行星捕获至日地平衡点、日地系统弱稳定边界区域和月球轨道附近的三种轨道设计方案,并对这些方案的参数特性进行了分析和比较。基于小推力转移方式,本文采用同伦优化算法,分别设计了从地球到小行星的小推力转移轨道以及通过三体动力学系统流形捕获至日地平衡点,通过弱稳定边界实现三体系统捕获和通过月球借力实现捕获的小推力转移轨道设计方案,并针对不同推力组合的工作模式,评估和分析了燃料消耗等捕获任务方案参数。针对从日地系统平衡点出发捕获小行星返回至日地系统平衡点的轨道设计问题,本文采用脉冲转移和小推力转移两种方式,并结合始末端流形逃逸和流形捕获的方法对小行星捕获轨道方案进行了设计,同时针对这两种方案所需的燃料消耗和飞行时间进行了对比和分析。以2006RH120小行星为目标星,本文基于小推力转移方式,并结合同伦优化算法和三体系统流形理论,给出了一套完整的小行星捕获任务轨道设计方案。同时结合小行星消旋等捕获操作对小行星捕获飞行组合体的质量、飞行时间、燃料消耗等重要设计参数进行了评估和分析。
[Abstract]:Asteroids have attracted much attention because of the residual material in the early solar system and abundant information about the evolution of the solar system. Capturing asteroids near Earth will not only help to obtain the material containing the original information of asteroids, but also be beneficial to the development and utilization of rich resources of asteroids. In this paper, based on the background of asteroid capture, the orbit design and optimization of asteroid capture based on the solar-terrestrial equilibrium point are studied. The main contents are as follows: in the selection of target stars, the characteristics of orbit are discussed in this paper. The physical and orbital characteristics of near-Earth asteroids are comprehensively analyzed in terms of spectral type and size distribution, and the selection conditions for capturing target stars are given. In combination with the energy requirements, the target stars suitable for the capture mission are selected. Based on the method of pulse transfer, this paper uses two-pulse and multi-pulse transfer, combined with manifold theory of three-body orbit dynamics system, weakly stable boundary theory and lunar borrowing theory, respectively, to give the target asteroid to the solar-earth equilibrium point. Three orbital design schemes for the weak stable boundary region of solar-earth system and near the lunar orbit are presented. The parametric characteristics of these schemes are analyzed and compared. Based on the small thrust transfer method, the homotopy optimization algorithm is used to design the small thrust transfer orbits from the Earth to the asteroid and to capture to the solar-earth equilibrium point through the manifold of the three-body dynamics system. The design scheme of the three-body system capture by weak stable boundary and the small thrust transfer orbit captured by the lunar force is realized. The parameters of the capture mission such as fuel consumption are evaluated and analyzed according to the different working modes of different thrust combinations. Aiming at the problem of orbit design for capturing asteroids from the equilibrium point of the solar-terrestrial system to the equilibrium point of the solar-terrestrial system, two methods of pulse transfer and small thrust transfer are used in this paper. Combined with the methods of end manifold escape and manifold capture, the asteroid capture orbit scheme is designed, and the fuel consumption and flight time of these two schemes are compared and analyzed. Based on the small thrust transfer method and the homotopy optimization algorithm and the manifold theory of the three-body system, a complete orbit design scheme for the asteroid capture mission is presented in this paper based on the 2006RH120 asteroid as the target star. At the same time, the mass, flight time, fuel consumption and other important design parameters of asteroid capture flight assembly are evaluated and analyzed.
【学位授予单位】：北京理工大学
【学位级别】：硕士
【学位授予年份】：2016
【分类号】：V412.41

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