國立虎尾科技大學 |

Design optimization of aircraft landing gear assembly under dynamic loading.

Record Type:	Language materials, manuscript : Monograph/item
Title/Author:	Design optimization of aircraft landing gear assembly under dynamic loading./
Author:	Wong, Jonathan Y. B.
Description:	1 online resource (92 pages)
Notes:	Source: Dissertation Abstracts International, Volume: 75-01C.
Contained By:	Dissertation Abstracts International75-01C.
Subject:	Mechanical engineering. -
Online resource:	click for full text (PQDT)

Design optimization of aircraft landing gear assembly under dynamic loading.
Wong, Jonathan Y. B.

Design optimization of aircraft landing gear assembly under dynamic loading. - 1 online resource (92 pages)

Source: Dissertation Abstracts International, Volume: 75-01C.

Thesis (M.A.Sc.)

Includes bibliographical references

As development cycles and prototyping iterations begin to decrease in the aerospace industry, it is important to develop and improve practical methodologies to meet all design metrics. This research presents an efficient methodology that applies high-fidelity multi-disciplinary design optimization techniques to commercial landing gear assemblies, for weight reduction, cost savings, and structural performance dynamic loading. Specifically, a slave link subassembly was selected as the candidate to explore the feasibility of this methodology. The design optimization process utilized in this research was sectioned into three main stages: setup, optimization, and redesign.

Electronic reproduction.
Ann Arbor, Mich. :
ProQuest,
2018

Mode of access: World Wide Web

Subjects--Topical Terms:

557493
Mechanical engineering.
Index Terms--Genre/Form:

554714
Electronic books.

Design optimization of aircraft landing gear assembly under dynamic loading.
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100 1 $a Wong, Jonathan Y. B. $3 1179284
245 1 0 $a Design optimization of aircraft landing gear assembly under dynamic loading.
264 0 $c 2017
300 $a 1 online resource (92 pages)
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500 $a Source: Dissertation Abstracts International, Volume: 75-01C.
502 $a Thesis (M.A.Sc.) $c Queen's University (Canada) $d 2017.
504 $a Includes bibliographical references
520 $a As development cycles and prototyping iterations begin to decrease in the aerospace industry, it is important to develop and improve practical methodologies to meet all design metrics. This research presents an efficient methodology that applies high-fidelity multi-disciplinary design optimization techniques to commercial landing gear assemblies, for weight reduction, cost savings, and structural performance dynamic loading. Specifically, a slave link subassembly was selected as the candidate to explore the feasibility of this methodology. The design optimization process utilized in this research was sectioned into three main stages: setup, optimization, and redesign.
520 $a The first stage involved the creation and characterization of the models used throughout this research. The slave link assembly was modelled with a simplified landing gear test, replicating the behavior of the physical system. Through extensive review of the literature and collaboration with Safran Landing Systems, dynamic and structural behavior for the system were characterized and defined mathematically. Once defined, the characterized behaviors for the slave link assembly were then used to conduct a Multi-Body Dynamic (MBD) analysis to determine the dynamic and structural response of the system. These responses were then utilized in a topology optimization through the use of the Equivalent Static Load Method (ESLM). The results of the optimization were interpreted and later used to generate improved designs in terms of weight, cost, and structural performance under dynamic loading in stage three. The optimized designs were then validated using the model created for the MBD analysis of the baseline design.
520 $a The design generation process employed two different approaches for post-processing the topology results produced. The first approach implemented a close replication of the topology results, resulting in a design with an overall peak stress increase of 74%, weight savings of 67%, and no apparent cost savings due to complex features present in the design. The second design approach focused on realizing reciprocating benefits for cost and weight savings. As a result, this design was able to achieve an overall peak stress increase of 6%, weight and cost savings of 36%, and 60%, respectively.
533 $a Electronic reproduction. $b Ann Arbor, Mich. : $c ProQuest, $d 2018
538 $a Mode of access: World Wide Web
650 4 $a Mechanical engineering. $3 557493
650 4 $a Aerospace engineering. $3 686400
655 7 $a Electronic books. $2 local $3 554714
690 $a 0548
690 $a 0538
710 2 $a ProQuest Information and Learning Co. $3 1178819
710 2 $a Queen's University (Canada). $3 1148613
773 0 $t Dissertation Abstracts International $g 75-01C.
856 4 0 $u http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=10670815 $z click for full text (PQDT)