系統識別號 | U0002-0107202005015500 |
---|---|
DOI | 10.6846/TKU.2020.00005 |
論文名稱(中文) | 複合材料輕航機身墜撞能量吸收分析 |
論文名稱(英文) | The Analysis of Crash Energy Absorption of Composites Light Aircraft Fuselage |
第三語言論文名稱 | |
校院名稱 | 淡江大學 |
系所名稱(中文) | 航空太空工程學系碩士班 |
系所名稱(英文) | Department of Aerospace Engineering |
外國學位學校名稱 | |
外國學位學院名稱 | |
外國學位研究所名稱 | |
學年度 | 108 |
學期 | 2 |
出版年 | 109 |
研究生(中文) | 易威廷 |
研究生(英文) | Wei-Ting Yi |
學號 | 603430058 |
學位類別 | 碩士 |
語言別 | 繁體中文 |
第二語言別 | |
口試日期 | 2020-06-04 |
論文頁數 | 98頁 |
口試委員 |
指導教授
-
陳步偉
委員 - 張永康 委員 - 沈坤耀 |
關鍵字(中) |
輕航機 適墜性 能量吸收 複合材料 |
關鍵字(英) |
Light Sport Aircraft Crashworthiness Energy Absorbing Composite |
第三語言關鍵字 | |
學科別分類 | |
中文摘要 |
隨著國際間的商業互動的頻繁、科技日新月異,航空器在這當中扮演著不可或缺的角色,航空產業的發展藉此也比已往更加的興盛,於此同時航空運輸除了便捷的方便性外,安全性成了人們是否選擇搭乘航空器的重要因素。然而,在近年來複合材料的使用及能量吸收的設計被廣泛應用在航空器上,當事故發生時航空器內成員的安全及存活率一直是航空界關心的議題,也因為適墜性的研究發展,得以讓機上成員的存活率獲得改善。 本研究使用金屬材料6061-T6及碳纖維複合材料T300/LTM45-EL作為機身結構材料,邊界條件的設定則分為兩部分(1)撞擊速度(2)撞擊角度;分別依據ASTM F2245-11所規範的 1.3Vso 下降速度,及AGATE所訂定的30°撞擊俯角,並使用Abaqus/Explicit 有限元素軟體進行動態墜撞分析。 本研究使用Zenith公司的STOL CH701作為研究模型,以Pro/Engineer建立3D機身模型並將原先STOL CH701後機身的桁架結構以及參考Flight Design C4之後機身管狀結構,應用有限元素軟體Abaqus將CH701原始後機身及改良後之後機身進行鋁合金及複合材料的動態墜撞分析,再使用改良後之後機身以及結合2015年劉家宏之前機身(座艙)模型後續整機墜撞之吸能分析。 在Abaqus軟體進行模擬分析後,CH701後機身桁架結構及方管結構的能量吸收分析,在使用6061-T鋁合金材料下,方管結構較原本桁架結構增加了48%的能量吸收,在使用T300碳纖維複合材料下,方管結構較原本桁架結構增加了37%的能量吸收。針對CH701機身進行改良進行動態墜撞分析中使用6061-T鋁合金材料下,方管結構較原本桁架結構增加了65%的能量吸收,在使用T300碳纖維複合材料下,方管結構較原本桁架結構增加了83%的能量吸收。 |
英文摘要 |
With the frequent international business interactions and rapid technological development, aircraft play an important role in this. The development of the aviation industry is also more prosperous than in the past. Safety has become an important factor in whether people choose to board the aircraft. However, in recent years, the use of composite materials and the design of energy absorption have been widely used in aircraft. When an accident occurs, the safety and survival rate of the members in the aircraft has always been a concern of the aviation industry. Because the development of crashworthiness, the survival rate of the members will improve on board. This study, metal materials 6061-T6 and carbon fiber composite material T300 / LTM45-EL were used as the fuselage structure materials. The boundary conditions were divided into two parts: (1) impact velocity (2) impact angle; The standard descent speed of 1.3Vso, and the 30 ° impact depression angle specified by AGATE, and Abaqus / Explicit finite element software is used for dynamic crash analysis. This study, Zenith ’s STOL CH701 was used as the research model, Pro / Engineer was used to create a 3D fuselage model, and the original STOL CH701 rear fuselage truss structure and the fuselage tubular structure after reference to Flight Design C4 were used. The finite element software Abaqus was used to convert the CH701 The original rear fuselage and the modified fuselage were subjected to dynamic crash analysis of aluminum alloy and composite materials, and then the improved fuselage and the energy absorption analysis of the subsequent complete crash of the fuselage (cockpit) model combined with the previous Liu Chia-Hung model in 2015. After simulation analysis by Abaqus software, energy absorption analysis of CH701 rear fuselage truss structure and square tube structure, using 6061-T aluminum alloy material, the square tube structure increased energy absorption by 48% compared with the truss structure. Under the T300 carbon fiber composite material, the square tube structure has increased energy absorption by 37% compared with the truss structure. The use of 6061-T aluminum alloy material in the dynamic crash analysis of the CH701 fuselage was improved, and the square tube structure increased energy absorption by 65% compared with the truss structure. With the use of T300 carbon fiber composite materials, the square tube structure was compared with the truss structure increases energy absorption by 83%. |
第三語言摘要 | |
論文目次 |
目錄 中文摘要................................................................................................... I 英文摘要...................................................................................................II 目錄..........................................................................................................III 圖目錄......................................................................................................IV 表目錄.......................................................................................................V 第一章 緒論 1 1.1前言.......................................................................................................1 1.2複合材料................................................................................................6 1.3 適墜性..................................................................................................24 1.4研究目的與方法......................................................................................26 第二章 文獻回顧.........................................................................................29 2.1各國對輕航機之定義...............................................................................29 2.2機身結構對於能量吸收之影響.................................................................33 2.3能量吸收...............................................................................................37 2.4結構最佳化設計用於結構改良.................................................................48 第三章 基礎理論..........................................................................................53 3.1 ABAQUS簡介.........................................................................................53 3.2 ABAQUS/CAE .....................................................................................53 3.3ABAQUS/OPTIMIZATION........................................................................57 3.4 ABAQUS與ANSYS數值分析最佳化..........................................................59 第四章 實驗設計...........................................................................................62 4.1研究流程..................................................................................................62 4.2模型建立.................................................................................................65 4.3材料參數及邊界條件設定.........................................................................69 4.4模型分析 .............................................................................................72 第五章、結論與建議.....................................................................................82 參考資料......................................................................................................84 附錄 論文簡要版...........................................................................................90 圖目錄 圖1-1 複合材料分類 .....................................................................................9 圖1-2 複合材料疊層示意圖...........................................................................11 圖1-3 複合材料纖維布結構...........................................................................12 圖1-4 複合材料三明治結構...........................................................................12 圖1-5 波音公司各機型材料使用情形..............................................................14 圖1-6 波音787材料分布圖............................................................................14 圖1-7 空中巴士各機型複材使用分布..............................................................15 圖1-8 空中巴士各機型複材使用情況..............................................................15 圖1-9 SR22 G3............................................................................................16 圖1-10 小鷹500...........................................................................................17 圖1-11 G120A..............................................................................................17 圖1-12 旋翼機葉片複材結構圖 .....................................................................18 圖1-13傳统結構用鋼之應力應變圖................................................................19 圖1-14 複合材料與鋁合金之應力應變比較圖..................................................22 圖1-15 不同材料的S-N曲線..........................................................................22 圖1-16雷擊損壞實例....................................................................................24 圖1-17 雷擊對複材機身之損傷......................................................................24 圖1-18研究流程圖........................................................................................28 圖2-1輕型飛機軟土墜落實驗 ......................................................................34 圖2-2 發動機架與防火牆改進設計.................................................................35 圖2-3 四種不同地板結構 .............................................................................35 圖2-4 Z-STRUTS墜落測試...........................................................................36 圖2-5 Z-STRUTS 破壞前後對照圖................................................................36 圖2-6 機身結構改良......................................................................................37 圖2-7力-位移圖之能量分析............................................................................38 圖2-8 複合材料與其他材料的吸能比較............................................................40 圖2-9 傳統飛機設計流程圖............................................................................49 圖2-10 拓墣最佳化用於設計流程圖 ...............................................................50 圖2-11原機鼻支架結構...................................................................................51 圖2-12拓墣最佳化後的機鼻支架結構..............................................................51 圖2-13尺寸最佳化後的機鼻支架結構..............................................................52 圖4-1 C4後機身尾管結構...............................................................................62 圖4-2研究流程圖...........................................................................................64 圖4-3 CH701三視圖.......................................................................................66 圖4-4 簡化後CH701模型圖.............................................................................68 圖4-5 後機身管狀結構模型.............................................................................69 圖4-6 AGATE定義之30度墜撞條件 ................................................................71 圖4-7 墜撞模擬之實心方塊.............................................................................72 圖4-8鋁合金方塊模擬能量圖..........................................................................73 圖4-9 複材方塊模擬能量圖..............................................................................74 圖4-10原後機身桁架結構模型..........................................................................76 圖4-11改良後之尾管結構模型..........................................................................76 圖4-12 CH701整機模型..................................................................................79 圖4-13 改良後之機身模型...............................................................................79 圖4-14 CH701鋁合金動態墜撞能量圖..............................................................79 圖4-15 CH701碳纖維複合材料動態墜撞能量圖................................................80 圖4-16 改良後之機身鋁合金動態墜撞能量圖....................................................80 圖4-17 改良後之機身碳纖維複合材料動態墜撞能量圖.......................................80 表目錄 表1-1 2003-2014年間我國航空器在國內外之飛航事故 ..................................2 表1-2 2014年美國航空器事故及死亡數............................................................4 表1-3 1995-2014年美國普通航空器總事故、死亡數.........................................5 表2-1 各國輕航機法規比較..............................................................................32 表2-2金屬與複合材料管之破碎試驗結果..........................................................41 表2-3鋁合金及複合材料試件在V=1.005 M/S下的SEA......................................45 表2-4鋁合金及複合材料試件在V=18.05 M/S下的SEA......................................46 表2-5鋁合金及複合材料試件在V=18.812 M/S下的SEA.....................................47 表4-1 STOL CH701的規格..............................................................................67 表4-2 ABAQUS單位對照表.............................................................................68 表4-3 鋁合金6061-T6材料參數......................................................................70 表4-4 碳纖維T300/LTM45-EL材料參數..........................................................70 表 4-5 撞擊角度與速度之參數 ........................................................................71 表4-6 CH701鋁合金、複材原始後機身模型與改良後之尾管模型吸能之比較 …77 表4-7 CH701鋁合金與複材整機改良前後吸能之比較......................................81 |
參考文獻 |
[1]「台灣飛安統計報告 2005-2014」,飛航安全調查委員會,2005-2014 年。 [2]「2014 preliminary aviation statistics」,National Transportation Safety Board Aviation Statistics for 2014, http://www.ntsb.gov/investigations/data/Pages/aviation_stats.aspx [3] Bhagwan D. Agarwal and Lawrence J. Broutman,”Analysis and Performance of Fiber Composites”, second edition [4] Taichi Fujii and Masaru Zako,”Fracture and mechanics of composite materials(1978)” [5]鄭明昌,複合材料單向薄片之「應力—應變」關係。 [6] Naval Education and Training Program Management Support Activity, Pensacola, Florida, “Aviation Structural Mechanic (H&S) 3&2”, http://navyaviation.tpub.com/14018/css/14018_596.htm [7] Tim Murphy,” Composite Construction: Decoding The Matrix”, October 19, 2013, http://www.cruisingworld.com/how/composite-construction-decoding-matrix [8] Salih Akour and Hussein Maaitah, ” Finite Element Analysis of Loading Area Effect on Sandwich Panel Behaviour Beyond the Yield Limit” ,October 10,2012 [9]「787 Aircraft Rescue & Firefighting Composite Structure」,April 2013 [10]Airbus Composite Training-VDP Conference-Frankfurt,October 17th 2007 [11] http://mohamed-loukil.blogspot.tw/2012_04_01_archive.html http://a380flightdeck.tumblr.com/post/85909891740/evolution-composite-application [12] MEG GODLEWSKI, Flying the Cirrus SR22 G3, SEPTEMBER 23, 2009, http://generalaviationnews.com/2009/09/23/flying-the-cirrus-sr22-g3/ [13]小鷹500飛機,西陸網,2014-11-10,http://junshi.xilu.com/news/xiaoying500feiji.html [14] Grob G120A Basic Trainer Aircraft, Germany, http://www.airforce-technology.com/projects/grob-g120a/ [15] Cssonawala IAMCHAITANYA Composites Material, Jun 3,2015, https://iamchaitanya.wordpress.com/2015/06/03/composite-materials/ [16] Andrew Halfpenny, “A Practical Discussion on Fatigue”, HBM nCode,http://www.ncode.com/tw/ [17] Micheal C.Y.Niu, “Composite airframe structures : practical design information and data.”,Technical Book Co, 1992. [18]疲勞極限, https://zh.wikipedia.org/wiki/%E7%96%B2%E5%8B%9E%E6 %A5%B5%E9%99%90 [19]雷擊之防護、檢驗與維修 ,2014年「飛行安全夏季刊」 [20]Dennis F. Shanahan, M.D., M.P.H., “Basic Principles of Crashworthiness”,RTO-EN-HFM-113.3, 2-3 November 2004. [21]美國聯邦航空總署, http://www.ecfr.gov/cgi-bin/text-idx?SID=4b5cc43b0d2e0e8ba712d0e84ca61c78&mc=true&node=se14.1.1_11&rgn=div8 [22]歐洲航空安全聯盟, https://www.easa.europa.eu/the-agency/faqs/light-sport-aircraft [23]交通部民用航空局,民用航空法, http://www.caa.gov.tw/APFile/big5/download/pliad/1424133119440.pdf [24]Terry H N. Nicholson. Design and test of an improved crashworthiness small composite airframe- phrase II report [R]. NASA SBIR Contract NAS1- 20427. Kansas: NASA. 1997. [25]李葳、徐惠民,「基於適墜性的輕型飛機結構設計改進方案」,南京航空航天大學學報,第40卷第4期,2008年8月。 [26]S. Heimbs, F. Strobl, P. Middendorf1, and J. M. Guimard, “Composite crash absorber for aircraft fuselage applications”, Structures Under Shock and Impact XI, WIT Transactions on The Built Environment, Vol. 113, 2010 [27] Marilyn Henderson and Steven J. Hooper, “Estimation of firewall loads due to soft soil impact”, AGATE-WP3.4-034026-087, March 1, 2002. [28] A.M.S. Hamouda, R.O. Saied, and F.M. Shuaeib “Energy Absorption Capacities of Square Tubular Structures.” Published in Revised, 2007. [29] 賴哲毅,「金屬與複合材料結構吸能特性之研究」,私立淡江大學航空太空工程學系碩士論文,2015年6月。 [30] Muniyasamy K. and Baskar M., “Topology Optimization of Aircraft Fuselage Structure”. World Academy of Science, Engineering and Technology 77 , 2013. [31]Rinku, A., Prashanth, R., and Kumar, R. O.,” Structural Optimization of Typical Light Transport Aircraft Components”, Technical Report HTC08, 2008. [32]ABAQUS Inc., Abaqus 6.12 Getting Started with Abaqus., 2005. [33]Dassault Systemes Simulia Corp.、士盟瑞其 CAE 團隊,「最新 Abaqus 實務入門」,全華圖書股份有限公司,2013。 [34] 張建華,丁磊的《ABAQUS基礎入門與案例精選》,電子工業出版社,2012.6 [35] 劉家宏,「複合材料輕航機之適墜性拓樸最佳化分析」,私立淡江大學航空太空工程學系碩士論文,2015年6月。 [36]MatWeb, http://http://www.matweb.com/ [37]Vaibhav A. Phadnis, Farrukh Makhdum, Anish Roy, Vadim V. Silberschmidt, “Drilling in carbon/epoxy composites:Experimental investigations and finite element implementation”.2013. [38] Steven J. Hooper, Marilyn Henderson, Waruna Seneviratne, “Design and Construction of a Crashworthy Composite Airframe”, AGATE-WP3.4-034026-089. Rev. A, March 1. 2002. [39]“Standard Specification for Design and Performance of a Light Sport Airplane”, , ASTMF2245F2245 -11 , 2012. |
論文全文使用權限 |
如有問題,歡迎洽詢!
圖書館數位資訊組 (02)2621-5656 轉 2487 或 來信