國立虎尾科技大學 |

Development of a Mission Design Tool for Computing Libration Point Formations Using Differential Corrections Initialized With a Genetic Algorithm.

紀錄類型:	書目-語言資料,手稿 : Monograph/item
正題名/作者:	Development of a Mission Design Tool for Computing Libration Point Formations Using Differential Corrections Initialized With a Genetic Algorithm./
作者:	Jennings, Donna Marie.
面頁冊數:	1 online resource (131 pages)
附註:	Source: Dissertations Abstracts International, Volume: 85-03, Section: B.
Contained By:	Dissertations Abstracts International85-03B.
標題:	Mechanical engineering. -
電子資源:	click for full text (PQDT)
ISBN:	9798380318723

Development of a Mission Design Tool for Computing Libration Point Formations Using Differential Corrections Initialized With a Genetic Algorithm.
Jennings, Donna Marie.

Development of a Mission Design Tool for Computing Libration Point Formations Using Differential Corrections Initialized With a Genetic Algorithm. - 1 online resource (131 pages)

Source: Dissertations Abstracts International, Volume: 85-03, Section: B.

Thesis (Ph.D.)--Missouri University of Science and Technology, 2023.

Includes bibliographical references

The growing interest in deep space spacecraft missions and distributed spacecraft formations has established the need for state-of-the-art advancements in the areas of relative dynamics and mission design. The focus of this research is to develop methods for identifying natural (i.e. ballistic) relative formation trajectories in the vicinity of the collinear libration points. A natural formation decreases the station keeping costs, lowering the consumption of spacecraft resources and extending mission lifetime. This research adapts both numerical and machine learning approaches to the problem of mission design. A genetic algorithm was first used to identify a multi-agent spacecraft formation in the vicinity of the collinear libration points that seeks to maximize a fitness function composed of the mission requirements. Due to the high computational cost, the algorithm approximates the spacecraft motion using an analytical approximation. This preserves the ability of the genetic algorithm to fully explore the design space and decreases the computational expense.Once the genetic algorithm identifies a suitable spacecraft formation, in order to improve the solution fidelity an iterative two-level targeter is initialized using the solution of interest identified by the genetic algorithm and the nonlinear equations of motion are propagated to identify each spacecraft's trajectory in the circular restricted three-body problem. The results show that the fourth-order approximation for the initialization step of the two-level targeter better estimates the nonlinear motion than a first-order approximation and results in minor changes to the final converged trajectory and preserves the desired orbit parameters. The converged trajectories from the two-level targeter were assessed for meeting mission success criteria, and the results indicate the same level or only slightly lower levels of mission success. Multiple case studies are presented that show applications and performances of the proposed mission design method.

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

Mode of access: World Wide Web

ISBN: 9798380318723Subjects--Topical Terms:

557493
Mechanical engineering.
Subjects--Index Terms:

Collinear libration pointsIndex Terms--Genre/Form:

554714
Electronic books.

Development of a Mission Design Tool for Computing Libration Point Formations Using Differential Corrections Initialized With a Genetic Algorithm.
LDR:03532ntm a22003977 4500 001 1145147
005 20240617111355.5
006 m o d
007 cr mn ---uuuuu
008 250605s2023 xx obm 000 0 eng d
020 $a 9798380318723
035 $a (MiAaPQ)AAI30571103
035 $a AAI30571103
040 $a MiAaPQ $b eng $c MiAaPQ $d NTU
100 1 $a Jennings, Donna Marie. $3 1470374
245 1 0 $a Development of a Mission Design Tool for Computing Libration Point Formations Using Differential Corrections Initialized With a Genetic Algorithm.
264 0 $c 2023
300 $a 1 online resource (131 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: Dissertations Abstracts International, Volume: 85-03, Section: B.
500 $a Advisor: Pernicka, Henry J.
502 $a Thesis (Ph.D.)--Missouri University of Science and Technology, 2023.
504 $a Includes bibliographical references
520 $a The growing interest in deep space spacecraft missions and distributed spacecraft formations has established the need for state-of-the-art advancements in the areas of relative dynamics and mission design. The focus of this research is to develop methods for identifying natural (i.e. ballistic) relative formation trajectories in the vicinity of the collinear libration points. A natural formation decreases the station keeping costs, lowering the consumption of spacecraft resources and extending mission lifetime. This research adapts both numerical and machine learning approaches to the problem of mission design. A genetic algorithm was first used to identify a multi-agent spacecraft formation in the vicinity of the collinear libration points that seeks to maximize a fitness function composed of the mission requirements. Due to the high computational cost, the algorithm approximates the spacecraft motion using an analytical approximation. This preserves the ability of the genetic algorithm to fully explore the design space and decreases the computational expense.Once the genetic algorithm identifies a suitable spacecraft formation, in order to improve the solution fidelity an iterative two-level targeter is initialized using the solution of interest identified by the genetic algorithm and the nonlinear equations of motion are propagated to identify each spacecraft's trajectory in the circular restricted three-body problem. The results show that the fourth-order approximation for the initialization step of the two-level targeter better estimates the nonlinear motion than a first-order approximation and results in minor changes to the final converged trajectory and preserves the desired orbit parameters. The converged trajectories from the two-level targeter were assessed for meeting mission success criteria, and the results indicate the same level or only slightly lower levels of mission success. Multiple case studies are presented that show applications and performances of the proposed mission design method.
533 $a Electronic reproduction. $b Ann Arbor, Mich. : $c ProQuest, $d 2024
538 $a Mode of access: World Wide Web
650 4 $a Mechanical engineering. $3 557493
650 4 $a Astrophysics. $3 646223
650 4 $a Aerospace engineering. $3 686400
653 $a Collinear libration points
653 $a Genetic algorithm
653 $a Mission design tool
653 $a Spacecraft formations
653 $a Two-level targeter
655 7 $a Electronic books. $2 local $3 554714
690 $a 0538
690 $a 0596
690 $a 0548
710 2 $a Missouri University of Science and Technology. $b Aerospace Engineering. $3 1467455
710 2 $a ProQuest Information and Learning Co. $3 1178819
773 0 $t Dissertations Abstracts International $g 85-03B.
856 4 0 $u http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=30571103 $z click for full text (PQDT)