國立虎尾科技大學 |

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

紀錄類型:	書目-語言資料,手稿 : Monograph/item
正題名/作者:	Low Thrust Transfers Between Periodic Orbits in the Earth-Moon Circular Restricted Three-Body Problem./
作者:	Patel, Rohan.
面頁冊數:	1 online resource (108 pages)
附註:	Source: Masters Abstracts International, Volume: 84-12.
Contained By:	Masters Abstracts International84-12.
標題:	Aerospace engineering. -
電子資源:	click for full text (PQDT)
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. - 1 online resource (108 pages)

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

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

Includes bibliographical references

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.

Electronic reproduction.
Ann Arbor, Mich. :
ProQuest,
2024

Mode of access: World Wide Web

ISBN: 9798379696702Subjects--Topical Terms:

686400
Aerospace engineering.
Subjects--Index Terms:

AstrodynamicsIndex Terms--Genre/Form:

554714
Electronic books.

Low Thrust Transfers Between Periodic Orbits in the Earth-Moon Circular Restricted Three-Body Problem.
LDR:03053ntm a22003977 4500 001 1145089
005 20240617111342.5
006 m o d
007 cr mn ---uuuuu
008 250605s2023 xx obm 000 0 eng d
020 $a 9798379696702
035 $a (MiAaPQ)AAI30425371
035 $a AAI30425371
040 $a MiAaPQ $b eng $c MiAaPQ $d NTU
100 1 $a Patel, Rohan. $3 1470301
245 1 0 $a Low Thrust Transfers Between Periodic Orbits in the Earth-Moon Circular Restricted Three-Body Problem.
264 0 $c 2023
300 $a 1 online resource (108 pages)
336 $a text $b txt $2 rdacontent
337 $a computer $b c $2 rdamedia
338 $a online resource $b cr $2 rdacarrier
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.
504 $a Includes bibliographical references
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.
533 $a Electronic reproduction. $b Ann Arbor, Mich. : $c ProQuest, $d 2024
538 $a Mode of access: World Wide Web
650 4 $a Aerospace engineering. $3 686400
650 4 $a Astrophysics. $3 646223
650 4 $a Computational physics. $3 1181955
653 $a Astrodynamics
653 $a Trajectory design
653 $a CR3BP
653 $a Earth-Moon system
653 $a DRO
655 7 $a Electronic books. $2 local $3 554714
690 $a 0538
690 $a 0596
690 $a 0216
710 2 $a ProQuest Information and Learning Co. $3 1178819
710 2 $a University of Colorado at Boulder. $b Aerospace Engineering. $3 1179005
773 0 $t Masters Abstracts International $g 84-12.
856 4 0 $u http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=30425371 $z click for full text (PQDT)