國立虎尾科技大學 |

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

紀錄類型:	書目-語言資料,手稿 : Monograph/item
正題名/作者:	Design of Low Thrust Space Trajectories Using Shape-Based Methods./
作者:	Vijayakumar, Madhusudan.
面頁冊數:	1 online resource (54 pages)
附註:	Source: Masters Abstracts International, Volume: 84-12.
Contained By:	Masters Abstracts International84-12.
標題:	Astronomy. -
電子資源:	click for full text (PQDT)
ISBN:	9798379743642

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

Design of Low Thrust Space Trajectories Using Shape-Based Methods. - 1 online resource (54 pages)

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

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

Includes bibliographical references

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.

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

Mode of access: World Wide Web

ISBN: 9798379743642Subjects--Topical Terms:

593935
Astronomy.
Subjects--Index Terms:

Low thrust trajectoriesIndex Terms--Genre/Form:

554714
Electronic books.

Design of Low Thrust Space Trajectories Using Shape-Based Methods.
LDR:02569ntm a22003737 4500 001 1145051
005 20240617111333.5
006 m o d
007 cr mn ---uuuuu
008 250605s2023 xx obm 000 0 eng d
020 $a 9798379743642
035 $a (MiAaPQ)AAI29066149
035 $a AAI29066149
040 $a MiAaPQ $b eng $c MiAaPQ $d NTU
100 1 $a Vijayakumar, Madhusudan. $3 1470261
245 1 0 $a Design of Low Thrust Space Trajectories Using Shape-Based Methods.
264 0 $c 2023
300 $a 1 online resource (54 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: Abdelkhalik, Ossama.
502 $a Thesis (M.S.)--Iowa State University, 2023.
504 $a Includes bibliographical references
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.
533 $a Electronic reproduction. $b Ann Arbor, Mich. : $c ProQuest, $d 2024
538 $a Mode of access: World Wide Web
650 4 $a Astronomy. $3 593935
650 4 $a Aerospace engineering. $3 686400
653 $a Low thrust trajectories
653 $a Mission design
653 $a Three body problem
653 $a Payload capability
655 7 $a Electronic books. $2 local $3 554714
690 $a 0538
690 $a 0606
710 2 $a Iowa State University. $b Aerospace Engineering. $3 1179169
710 2 $a ProQuest Information and Learning Co. $3 1178819
773 0 $t Masters Abstracts International $g 84-12.
856 4 0 $u http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=29066149 $z click for full text (PQDT)