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Design of Low Thrust Space Trajector...

Vijayakumar, Madhusudan.

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Design of Low Thrust Space Trajectories Using Shape-Based Methods.

Record Type:	Electronic resources : Monograph/item
Title/Author:	Design of Low Thrust Space Trajectories Using Shape-Based Methods./
Author:	Vijayakumar, Madhusudan.
Published:	Ann Arbor : ProQuest Dissertations & Theses, : 2023,
Description:	54 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=29066149
ISBN:	9798379743642

Design of Low Thrust Space Trajectories Using Shape-Based Methods.
Vijayakumar, Madhusudan.

Design of Low Thrust Space Trajectories Using Shape-Based Methods. - Ann Arbor : ProQuest Dissertations & Theses, 2023 - 54 p.

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

Thesis (M.S.)--Iowa State University, 2023.

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

Space missions implementing continuous low-thrust propulsion are gaining popularity due to their increased payload capability. However, trajectory design for such missions is extremely complex and time-consuming. Additionally, the design space is very large for low thrust trajectories, and the optimal solvers' convergence radius is very small. The numerical methods employed to obtain these trajectories are extremely sensitive to initial guesses. Thus, the rapid generation of good initial guess trajectories becomes a key player in obtaining fruitful convergence on optimal control tools. The Finite Fourier Series (FFS) Shape-Based Method is one method capable of generating initial guess trajectories. This thesis builds on the existing FFS shape-based method to improve the transfer cost of planar trajectories by making a systematic modification. The applicability of this method was tested for planar two-body and three-body problems. Different design scenarios were studied, like rendezvous and orbit insertion in geocentric, cislunar, and interplanetary space. This new approach can effectively handle thrust acceleration constraints while meeting transfer requirements. The proposed method meets design constraints at a lower cost than the original formulation.

ISBN: 9798379743642Subjects--Topical Terms:

1002622
Aerospace engineering.
Subjects--Index Terms:

Low thrust trajectories

Design of Low Thrust Space Trajectories Using Shape-Based Methods.
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100 1 $a Vijayakumar, Madhusudan. $0 (orcid)0000-0002-3857-2894 $3 3766915
245 1 0 $a Design of Low Thrust Space Trajectories Using Shape-Based Methods.
260 1 $a Ann Arbor : $b ProQuest Dissertations & Theses, $c 2023
300 $a 54 p.
500 $a Source: Masters Abstracts International, Volume: 84-12.
500 $a Advisor: Abdelkhalik, Ossama.
502 $a Thesis (M.S.)--Iowa State University, 2023.
506 $a This item must not be sold to any third party vendors.
520 $a Space missions implementing continuous low-thrust propulsion are gaining popularity due to their increased payload capability. However, trajectory design for such missions is extremely complex and time-consuming. Additionally, the design space is very large for low thrust trajectories, and the optimal solvers' convergence radius is very small. The numerical methods employed to obtain these trajectories are extremely sensitive to initial guesses. Thus, the rapid generation of good initial guess trajectories becomes a key player in obtaining fruitful convergence on optimal control tools. The Finite Fourier Series (FFS) Shape-Based Method is one method capable of generating initial guess trajectories. This thesis builds on the existing FFS shape-based method to improve the transfer cost of planar trajectories by making a systematic modification. The applicability of this method was tested for planar two-body and three-body problems. Different design scenarios were studied, like rendezvous and orbit insertion in geocentric, cislunar, and interplanetary space. This new approach can effectively handle thrust acceleration constraints while meeting transfer requirements. The proposed method meets design constraints at a lower cost than the original formulation.
590 $a School code: 0097.
650 4 $a Aerospace engineering. $3 1002622
650 4 $a Astronomy. $3 517668
653 $a Low thrust trajectories
653 $a Mission design
653 $a Three body problem
653 $a Payload capability
690 $a 0538
690 $a 0606
710 2 $a Iowa State University. $b Aerospace Engineering. $3 1023643
773 0 $t Masters Abstracts International $g 84-12.
790 $a 0097
791 $a M.S.
792 $a 2023
793 $a English
856 4 0 $u https://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=29066149