本文選題：開縫襯套　切入點(diǎn)：冷擠壓　出處：《南京航空航天大學(xué)》2016年碩士論文　論文類型：學(xué)位論文

【摘要】：隨著C919大客機(jī)成功總裝下線,我國民用航空事業(yè)的發(fā)展又邁開了新的篇章。然而,民用航空事業(yè)的迅速發(fā)展,必然加大對(duì)飛機(jī)疲勞壽命使用要求的提高。開縫襯套冷擠壓強(qiáng)化技術(shù)能夠顯著提高飛機(jī)上緊固孔的疲勞壽命,因此該技術(shù)正被廣泛地應(yīng)用于航空工業(yè)領(lǐng)域。本文針對(duì)直徑在10mm以下范圍的開縫襯套進(jìn)行了冷擠壓數(shù)值模擬仿真,研究該技術(shù)對(duì)帶孔試件疲勞增壽效果的影響,主要工作及取得的成果如下:1.建立了帶孔試件冷擠壓強(qiáng)化有限元模擬仿真模型,對(duì)不同材料的帶孔試件進(jìn)行有限元模擬仿真。研究不帶開縫襯套與帶開縫襯套時(shí),冷擠壓強(qiáng)化工藝對(duì)不同材料帶孔試件孔周圍切向應(yīng)力分布的影響;同時(shí),改變擠壓量,研究擠壓量的變化對(duì)孔周圍切向應(yīng)力分布的影響。2.在獲得有限元仿真結(jié)果的基礎(chǔ)上,對(duì)7050鋁合金帶孔試件進(jìn)行了全壽命疲勞仿真和應(yīng)變壽命疲勞仿真,獲得了襯套有無、擠壓量變化、疲勞載荷變化等因素對(duì)其疲勞壽命的影響情況;建立了TC4鈦合金帶孔試件冷擠壓強(qiáng)化全壽命疲勞仿真模型,通過改變襯套的有無、擠壓量的大小以及疲勞載荷的大小來研究這些因素對(duì)試件疲勞壽命的影響情況。3.建立了7050鋁合金和TC4鈦合金帶孔試件在不同擠壓量和不同載荷條件下經(jīng)開縫襯套冷擠壓強(qiáng)化以后疲勞裂紋擴(kuò)展仿真模型,獲得帶孔試件的疲勞裂紋擴(kuò)展仿真壽命。通過獲得的疲勞壽命仿真值,將疲勞裂紋擴(kuò)展仿真壽命結(jié)果與全壽命疲勞仿真和應(yīng)變壽命疲勞仿真結(jié)果作比較。4.就全壽命疲勞仿真模型、應(yīng)變壽命疲勞仿真模型以及疲勞裂紋擴(kuò)展仿真模型角度著手,從疲勞壽命增強(qiáng)倍數(shù)方面分析,研究開縫襯套冷擠壓強(qiáng)化技術(shù)對(duì)不同材料的帶孔試件疲勞增壽效果的影響。5.在VS2010開發(fā)平臺(tái)上,借助MFC類庫,使用C++語言,結(jié)合ABAQUS腳本文件、MATLAB引擎、SQL語言,綜合開發(fā)了一套完整的開縫襯套冷擠壓強(qiáng)化疲勞壽命預(yù)測(cè)系統(tǒng),該系統(tǒng)集ABAQUS二次開發(fā)平臺(tái)、疲勞壽命預(yù)測(cè)平臺(tái)和數(shù)據(jù)庫管理平臺(tái)于一體,將本文研究的方法進(jìn)行了優(yōu)化,內(nèi)容進(jìn)行了匯總。
[Abstract]:With the successful final assembly of the C919 passenger plane, the development of civil aviation in China has opened a new chapter. However, the rapid development of civil aviation, It is necessary to increase the requirements for aircraft fatigue life. The cold extrusion strengthening technology of slit bushing can significantly improve the fatigue life of fastening holes in aircraft. Therefore, this technology is being widely used in aviation industry. In this paper, the cold extrusion numerical simulation of slit bushing with diameter less than 10mm is carried out to study the effect of this technology on fatigue life increase of specimen with holes. The main work and results obtained are as follows: 1. The finite element simulation model of cold extrusion strengthening specimen with holes is established, and the finite element simulation of different materials with holes is carried out. When there is no slit bushing and slotted bushing, The influence of cold extrusion strengthening process on the tangential stress distribution around the hole of different materials with holes, and the influence of the change of extrusion quantity on the distribution of tangential stress around the hole by changing the extrusion amount. 2. On the basis of the finite element simulation results, The full life fatigue simulation and strain life fatigue simulation of 7050 aluminum alloy specimen with holes were carried out, and the influence of the factors such as the existence of bushing, the change of extrusion amount and the change of fatigue load on the fatigue life of 7050 aluminum alloy specimen were obtained. In this paper, the fatigue simulation model of cold extrusion strengthened whole life of TC4 titanium alloy specimens with holes is established. By changing the existence or absence of bushing, The influence of these factors on fatigue life of specimens was studied by the size of extrusion amount and fatigue load. 3. The slotted bushing of 7050 aluminum alloy and TC4 titanium alloy with holes was established under different extrusion and load conditions. Simulation model of fatigue crack growth after cold extrusion, The fatigue crack propagation simulation life of the specimen with holes is obtained. The simulation results of fatigue crack growth are compared with those of full life fatigue simulation and strain life fatigue simulation. 4. From the point of view of full life fatigue simulation model, strain life fatigue simulation model and fatigue crack growth simulation model, Based on the analysis of fatigue life enhancement multiple, the effect of cold extrusion strengthening technology of slit bushing on fatigue life increasing effect of different materials with holes is studied. 5. On the VS2010 development platform, with the help of MFC class library, C language is used. Combined with ABAQUS script file and ABAQUS engine language, a set of integrated cold extrusion strengthened fatigue life prediction system for slit bushing is developed. The system integrates ABAQUS secondary development platform, fatigue life prediction platform and database management platform. The method studied in this paper is optimized and the content is summarized.
【學(xué)位授予單位】：南京航空航天大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2016
【分類號(hào)】：V215.5

【參考文獻(xiàn)】

相關(guān)期刊論文 前10條

1 王亮;汝繼剛;李惠曲;伊琳娜;劉銘;;孔擠壓強(qiáng)化工藝對(duì)7A12鋁合金組織及疲勞性能影響的研究[J];新技術(shù)新工藝;2014年11期

2 秦鋒英;劉萬春;;基于ABAQUS的TC21結(jié)構(gòu)件孔擠壓強(qiáng)化模擬分析[J];航空精密制造技術(shù);2014年02期

3 喬紅超;趙吉賓;郭慶耀;;激光沖擊強(qiáng)化激光器的研制[J];強(qiáng)激光與粒子束;2013年09期

4 薛巍;;帶開縫襯套的冷擴(kuò)孔擠壓工藝[J];中國高新技術(shù)企業(yè);2011年34期

5 王強(qiáng);陳雪梅;張文光;王欣;;A-100鋼開縫襯套孔擠壓強(qiáng)化殘余應(yīng)力場(chǎng)[J];中國表面工程;2011年05期

6 郭攀成;屈蘭鋒;;現(xiàn)代抗疲勞制造應(yīng)用技術(shù)研究與發(fā)展[J];蘭州工業(yè)高等�？茖W(xué)校學(xué)報(bào);2011年03期

7 張強(qiáng);馬永;李四超;;基于Python的ABAQUS二次開發(fā)方法與應(yīng)用[J];艦船電子工程;2011年02期

8 黃金昌;于雷;;開縫襯套釘孔擠壓強(qiáng)化技術(shù)研究[J];飛機(jī)設(shè)計(jì);2010年05期

9 楊洪源;劉文s，

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