低推力推進式宇宙機による地球捕獲小惑星探査の軌道設計

本研究系针对行星际小卫星飞行任务，提出一套系统化的方法，以产生多重绕月序列的初步猜测。太阳的第三体摄动起着重要的作用，基本上提供了自由v之间的月球摆动。作为第一种方法，提出了经典的Tisserand-Pointcar ′ e图的扩展，其中可以估计飞掠之间的太阳扰动的潜在增益。其次，根据Lantoine和McElrath提出的方法，使用连续方法生成月-月转移数据库。新的家庭与多个革命和家庭接近天平动点轨道的产生。可以访问数据库并检索传输，以类似于Lambert问题求解器的方式快速生成序列。介绍了两个实际例子：转移到地球-月球L2点，以及“命运”使命启动转移到小行星辉腾的逃逸战略。

Studied in this research is a systematic approach to generate first guesses of multiple lunar swing-by sequences for interplanetary small satellite missions. The Sun third body perturbation plays an important role essentially providing free v between lunar swing-bys. As a first approach, an extension of the classical Tisserand-Pointcar´e graph is presented, in which the potential gains by solar perturbation between flybys can be estimated. Secondly, following an approach proposed by Lantoine & McElrath, a database of Moon-to-Moon transfers is generated with a continuation method. New families with multiple revolutions and families close to libration point orbits are generated. The database can be accessed and transfers retrieved to quickly generate sequences in similar fashion to a Lambert problem solver. Two practical examples are presented: a transfer to the Earth-Moon L2 point, and an escape strategy for the DESTINY mission to initiate the transfer to asteroid Phaeton.