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Low Thrust Transfers Between Periodi...

Patel, Rohan.

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Low Thrust Transfers Between Periodic Orbits in the Earth-Moon Circular Restricted Three-Body Problem.

Record Type:	Electronic resources : Monograph/item
Title/Author:	Low Thrust Transfers Between Periodic Orbits in the Earth-Moon Circular Restricted Three-Body Problem./
Author:	Patel, Rohan.
Published:	Ann Arbor : ProQuest Dissertations & Theses, : 2023,
Description:	108 p.
Notes:	Source: Masters Abstracts International, Volume: 84-12.
Contained By:	Masters Abstracts International84-12.
Subject:	Aerospace engineering. -
Online resource:	https://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=30425371
ISBN:	9798379696702

Low Thrust Transfers Between Periodic Orbits in the Earth-Moon Circular Restricted Three-Body Problem.
Patel, Rohan.

Low Thrust Transfers Between Periodic Orbits in the Earth-Moon Circular Restricted Three-Body Problem. - Ann Arbor : ProQuest Dissertations & Theses, 2023 - 108 p.

Source: Masters Abstracts International, Volume: 84-12.

Thesis (M.S.)--University of Colorado at Boulder, 2023.

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

With growing interest in cislunar exploration, the importance of trajectory design in this environment has become prevalent. The Circular Restricted Three Body Problem (CR3BP) offers a useful dynamical model to incorporate the gravitational influence from the Earth and Moon in this regime. Several fundamental solutions exist in this model that are beneficial for trajectory design. One type of motion is periodic orbits that are repeating with respect to the motion of the Earth and Moon about the system barycenter. A wide variety of stable and unstable periodic orbits have been identified around equilibrium points and both celestial bodies. Transfers between periodic orbits can help facilitate cislunar exploration objectives for human spaceflight, space domain awareness, and science missions. Thus, this thesis focuses on designing transfers for low thrust spacecraft between periodic orbits in the Earth-Moon CR3BP.Insights of the dynamics are leveraged along with strategies to form initial guess transfer paths between two periodic orbits. Shooting schemes are employed to produce continuous transfers for each initial guess, and continuation is used compute potentially many transfers of interest. Finally, direct optimization is used to compute locally fuel-optimal transfers. The process of identifying potential initial guess paths, recovering a continuous solution, and ultimately an optimal trajectory is shown to be an effective method to find transfers between periodic orbits. Example cases are demonstrated between subsets of the L1 and L2 halo periodic orbit family and a near rectilinear halo orbit (NRHO) to a distant retrograde orbit (DRO) in the Earth-Moon system.

ISBN: 9798379696702Subjects--Topical Terms:

1002622
Aerospace engineering.
Subjects--Index Terms:

Astrodynamics

Low Thrust Transfers Between Periodic Orbits in the Earth-Moon Circular Restricted Three-Body Problem.
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020 $a 9798379696702
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100 1 $a Patel, Rohan. $3 3766953
245 1 0 $a Low Thrust Transfers Between Periodic Orbits in the Earth-Moon Circular Restricted Three-Body Problem.
260 1 $a Ann Arbor : $b ProQuest Dissertations & Theses, $c 2023
300 $a 108 p.
500 $a Source: Masters Abstracts International, Volume: 84-12.
500 $a Advisor: Bosanac, Natasha.
502 $a Thesis (M.S.)--University of Colorado at Boulder, 2023.
506 $a This item must not be sold to any third party vendors.
520 $a With growing interest in cislunar exploration, the importance of trajectory design in this environment has become prevalent. The Circular Restricted Three Body Problem (CR3BP) offers a useful dynamical model to incorporate the gravitational influence from the Earth and Moon in this regime. Several fundamental solutions exist in this model that are beneficial for trajectory design. One type of motion is periodic orbits that are repeating with respect to the motion of the Earth and Moon about the system barycenter. A wide variety of stable and unstable periodic orbits have been identified around equilibrium points and both celestial bodies. Transfers between periodic orbits can help facilitate cislunar exploration objectives for human spaceflight, space domain awareness, and science missions. Thus, this thesis focuses on designing transfers for low thrust spacecraft between periodic orbits in the Earth-Moon CR3BP.Insights of the dynamics are leveraged along with strategies to form initial guess transfer paths between two periodic orbits. Shooting schemes are employed to produce continuous transfers for each initial guess, and continuation is used compute potentially many transfers of interest. Finally, direct optimization is used to compute locally fuel-optimal transfers. The process of identifying potential initial guess paths, recovering a continuous solution, and ultimately an optimal trajectory is shown to be an effective method to find transfers between periodic orbits. Example cases are demonstrated between subsets of the L1 and L2 halo periodic orbit family and a near rectilinear halo orbit (NRHO) to a distant retrograde orbit (DRO) in the Earth-Moon system.
590 $a School code: 0051.
650 4 $a Aerospace engineering. $3 1002622
650 4 $a Astrophysics. $3 535904
650 4 $a Computational physics. $3 3343998
653 $a Astrodynamics
653 $a Trajectory design
653 $a CR3BP
653 $a Earth-Moon system
653 $a DRO
690 $a 0538
690 $a 0596
690 $a 0216
710 2 $a University of Colorado at Boulder. $b Aerospace Engineering. $3 1030473
773 0 $t Masters Abstracts International $g 84-12.
790 $a 0051
791 $a M.S.
792 $a 2023
793 $a English
856 4 0 $u https://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=30425371