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    Please use this identifier to cite or link to this item: http://tkuir.lib.tku.edu.tw:8080/dspace/handle/987654321/88060

    Title: 輕型運動飛機起落架損傷容忍分析
    Other Titles: Damage tolerance analysis of light-sport aircraft landing gear
    Authors: 蕭鈞元;Siao, Jyun-Yuan
    Contributors: 淡江大學航空太空工程學系碩士班
    Keywords: 損傷容忍;裂紋擴展;有限元素法;輕航機;damage tolerance;crack propagation;Finite Element;light aircraft
    Date: 2012
    Issue Date: 2013-04-13 11:58:56 (UTC+8)
    Abstract: 隨著飛機的發展,飛機設計的概念也不斷進行修正。幾次重大飛行事故顯示安全壽期與失效安全的設計概念都無法保證飛機結構的安全。目前的FAA航空法規中,任何失效後會導致重大事故的結構件均應視為損傷容忍規範的結構件。起落架為輕航機最主要的結構件之一,因此其損傷容忍分析是相當重要的。
    The philosophies of aircraft design were changed with aircraft development. Several aviation accidents show that safe-life design and fail-safe design cannot ensure structure safety of operation. In Federal Aviation Regulations, for each part of the structure which could contribute to a catastrophic failure must also be evaluated by damage-tolerance analysis. Landing gear is one of major light-sports aircraft structures, so damage-tolerance analysis is important.

    The purpose of this study is to use finite element analysis software FRANC2D and crack growth analysis software AFGROW to simulate damage-tolerance behavior in light-sports aircraft landing gear, and discuss the results of initial crack locations and materials. Materials are aluminum alloy 6061-T6, 6061-T651, 2024-T3, 7075-T6, titanium Ti-6Al-4V and alloy steel 4340. Landing gear load is 450kg from CH701 maximum take-off weight.

    The results showed that crack propagation life of 6061-T6 landing gear was about 48,000 cycles with 1mm initial crack and 450kg loading. Compare with 6061-T6, crack propagation life of 7075-T6, 2024-T3, 6061-T651 landing gear increased by 21%, 156%, 236% respectively. The crack propagation life of titanium and alloy steel were much higher than aluminum. Life of Ti-6Al-4V was 15 times higher than 6061-T6,and life of 4340 steel was 27 times higher than 6061-T6.
    Appears in Collections:[航空太空工程學系暨研究所] 學位論文

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