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Exploring the Geometry of Departure Trajectories from an Earth-Moon near Rectilinear Halo Orbit.

紀錄類型:	書目-語言資料,印刷品 : Monograph/item
正題名/作者:	Exploring the Geometry of Departure Trajectories from an Earth-Moon near Rectilinear Halo Orbit./
作者:	Joyner, Maxwell.
出版者:	Ann Arbor : ProQuest Dissertations & Theses, : 2022,
面頁冊數:	113 p.
附註:	Source: Masters Abstracts International, Volume: 84-03.
Contained By:	Masters Abstracts International84-03.
標題:	Mechanical engineering. -
電子資源:	http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=29323898
ISBN:	9798351430232

Exploring the Geometry of Departure Trajectories from an Earth-Moon near Rectilinear Halo Orbit.
Joyner, Maxwell.

Exploring the Geometry of Departure Trajectories from an Earth-Moon near Rectilinear Halo Orbit. - Ann Arbor : ProQuest Dissertations & Theses, 2022 - 113 p.

Source: Masters Abstracts International, Volume: 84-03.

Thesis (M.S.)--University of Colorado at Boulder, 2022.

This item must not be sold to any third party vendors.

To facilitate NASA’s Artemis program involving the first crewed lunar missions in over fifty years, current plans are to establish an outpost near the Earth-Moon L2 Lagrange point: the Gateway. The purpose of this deep space station is to serve as a staging area for missions to the lunar surface as well as further into the solar system. An L2 southern near rectilinear halo orbit (NRHO) was selected to place the Gateway for a number of advantages. This thesis centers on analyzing thrust-enabled departure trajectories from this NRHO using both the circular restricted three body problem (CR3BP) and an ephemeris model. Data sets of trajectories, generated in each of the CR3BP and ephemeris models using the General Mission Analysis Tool (GMAT), are divided into classes based on whether the solutions experience an escape through L1, L2, or a lunar surface impact. Each of these data sets is input to an agglomerative hierarchical clustering algorithm to separate solutions with distinct geometries. This approach is able to identify several types of departure trajectories in the CR3BP as well as the ephemeris model for each event class with potential applications for operations in cislunar space.

ISBN: 9798351430232Subjects--Topical Terms:

557493
Mechanical engineering.
Subjects--Index Terms:

Cislunar Space

Exploring the Geometry of Departure Trajectories from an Earth-Moon near Rectilinear Halo Orbit.
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300 $a 113 p.
500 $a Source: Masters Abstracts International, Volume: 84-03.
500 $a Advisor: Bosanac, Natasha.
502 $a Thesis (M.S.)--University of Colorado at Boulder, 2022.
506 $a This item must not be sold to any third party vendors.
520 $a To facilitate NASA’s Artemis program involving the first crewed lunar missions in over fifty years, current plans are to establish an outpost near the Earth-Moon L2 Lagrange point: the Gateway. The purpose of this deep space station is to serve as a staging area for missions to the lunar surface as well as further into the solar system. An L2 southern near rectilinear halo orbit (NRHO) was selected to place the Gateway for a number of advantages. This thesis centers on analyzing thrust-enabled departure trajectories from this NRHO using both the circular restricted three body problem (CR3BP) and an ephemeris model. Data sets of trajectories, generated in each of the CR3BP and ephemeris models using the General Mission Analysis Tool (GMAT), are divided into classes based on whether the solutions experience an escape through L1, L2, or a lunar surface impact. Each of these data sets is input to an agglomerative hierarchical clustering algorithm to separate solutions with distinct geometries. This approach is able to identify several types of departure trajectories in the CR3BP as well as the ephemeris model for each event class with potential applications for operations in cislunar space.
590 $a School code: 0051.
650 4 $a Mechanical engineering. $3 557493
650 4 $a Engineering. $3 561152
650 4 $a Aerospace engineering. $3 686400
653 $a Cislunar Space
653 $a Hierarchical agglomerative clustering
653 $a Lagrangian point
653 $a Low thrust trajectory
653 $a Near rectilinear halo orbit
653 $a Three body problem
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690 $a 0537
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710 2 $a University of Colorado at Boulder. $b Aerospace Engineering. $3 1179005
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793 $a English
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