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首页> 外文学位 >Mission Design, Guidance, and Navigation of a Callisto-Io-Ganymede Triple Flyby Jovian Capture.
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Mission Design, Guidance, and Navigation of a Callisto-Io-Ganymede Triple Flyby Jovian Capture.

机译：Callisto-Io-Ganymede Triple Flyby Jovian Capture的任务设计，指导和导航。

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摘要

Use of a triple-satellite-aided capture maneuver to enter Jovian orbit reduces insertion DeltaV and provides close flyby science opportunities at three of Jupiter's four large Galilean moons. This capture can be performed while maintaining appropriate Jupiter standoff distance and setting up a suitable apojove for plotting an extended tour.;This paper has three main chapters, the first of which discusses the design and optimization of a triple-flyby capture trajectory. A novel triple-satellite-aided capture uses sequential flybys of Callisto, Io, and Ganymede to reduce the DeltaV required to capture into orbit about Jupiter. An optimal broken-plane maneuver is added between Earth and Jupiter to form a complete chemical/impulsive interplanetary trajectory from Earth to Jupiter. Such a trajectory can yield significant fuel savings over single and double-flyby capture schemes while maintaining a brief and simple interplanetary transfer phase.;The second chapter focuses on the guidance and navigation of such trajectories in the presence of spacecraft navigation errors, ephemeris errors, and maneuver execution errors. A powered-flyby trajectory correction maneuver (TCM) is added to the nominal trajectory at Callisto and the nominal Jupiter orbit insertion (JOI) maneuver is modified to both complete the capture and target the Ganymede flyby. A third TCM is employed after all the flybys to act as a JOI cleanup maneuver. A Monte Carlo simulation shows that the statistical DeltaV required to correct the trajectory is quite manageable and the flyby characteristics are very consistent. The developed methods maintain flexibility for adaptation to similar launch, cruise, and capture conditions.;The third chapter details the methodology and results behind a completely separate project to design and optimize an Earth-orbiting three satellite constellation to perform very long baseline interferometry (VLBI) as part of the 8th annual Global Trajectory Optimisation Competition (GTOC8). A script is designed to simulate the prescribed constellation and record its observations; the observations made are scored according to a provided performance index.
机译：使用三颗卫星辅助的捕获机动进入朱维安轨道将减少插入DeltaV，并为木星的四个大型伽利略卫星中的三个提供近距离飞越科学机会。可以在保持适当的木星对峙距离并设置适当的aphojove来绘制扩展巡回图的同时执行捕获。本文共分三章，第一章讨论了三重飞越捕获轨迹的设计和优化。一种新颖的三颗卫星辅助捕获技术，利用Callisto，Io和Ganymede的连续飞越来减少捕获进入木星轨道所需的DeltaV。在地球和木星之间添加了最佳的断面操纵，以形成从地球到木星的完整化学/脉冲星际轨道。这样的轨迹可以比单飞和双飞捕获方案节省大量燃料，同时保持简短而简单的行星际转移阶段。第二章着重介绍在存在航天器导航误差，星历误差，和操纵执行错误。在卡利斯托（Callisto）的标称轨迹上添加了动力飞越轨迹校正操纵（TCM），并对标称木星轨道插入（JOI）操纵进行了修改，以完成捕获并瞄准木卫三飞越。在所有飞越之后采用第三个TCM作为JOI清理机动。蒙特卡洛模拟显示，校正轨迹所需的统计DeltaV相当容易管理，飞越特性也非常一致。所开发的方法保持了适应类似发射，巡航和捕获条件的灵活性。第三章详细介绍了一个完全独立的项目的方法和结果，该项目设计和优化了绕地球运行的三个卫星星座，以执行非常长的基线干涉测量（VLBI） ），这是第八届年度全球航迹优化大赛（GTOC8）的一部分。设计脚本来模拟指定的星座并记录其观测结果；根据提供的性能指标对观察结果进行评分。

著录项

  • 作者

    Didion, Alan M.;

  • 作者单位

    West Virginia University.;

  • 授予单位 West Virginia University.;
  • 学科 Aerospace engineering.;Mechanical engineering.;Physics.
  • 学位 M.S.
  • 年度 2015
  • 页码 80 p.
  • 总页数 80
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
  • 关键词

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