，计算材料学：
修复金属板裂纹的复合材料补片正交优化
穆志韬牛勇赵霞？（1海军航空工程学院青岛校区，青岛266041）
(2青岛大学，青岛266061）
文摘基于Abaqus软件建立了金属板裂纹复合材料补片修复结构的有限元模型。以应力强度因子(SIF)为判据，利用L（3")型正交实验考察了各补片参数对修复效果的影响。结果表明：在99%置信度水平下，补片厚度的贡缺率为68.77%，铺层顺序的贡献率为29.59%，而补片长度对修复效果的影响不明显。结合工程应用实际与正交分析结果，利用设计好的补片对含中心贯穿裂纹的铝合金板进行了修复，并对修复结构进行了静强度测试。结果表明：修补后静强度为未修复裂纹板的1.32倍，恢复至完好板的97.2%，延伸率为未修复裂纹板的2.24倍，恢复至完好板的50.7%。结论：选用长度为40mm，厚度为1.2mm，铺层顺序为[0°/90°] 的正方形补片时修补效果最好。
关键词复合材料胶接修复，有限元分析，正交分析，贡献率，静拉伸试验
中图分类号：TB330.1；TG497
D0I:10.12044/j.issn.10072330.2017.03.004
OrthogonalOptimizationofCompositePatchfor
RepairofCrackedMetallicPlate MUZhitao'NIUYong'ZHAOXia
(1Qingdao Campus,Naval Aeronautical and Astronautical University，Qingdao266041）
(2 Qingdao University,Qingdao 266061)
Abstract The finite element model is developed by Abaqus for analyzing the fracture problem of cracked metal-lic plate repaired with the double-side adhesively bonded composite patches, in which the thermal residual stresses is also contained, and the stress intensify factor(SIF) is used to evaluate the repair effect.Meanwhile, with the help of orthogonal table L,(3'), the parameter of the patches,which influence the repair effect,has also been evaluated. The orthogonal analysis result shows that,in confidence level of 99%, the contribution ratio of lay-up direction and patch thickness are 68.77% and 29.59% respectively.Meanwhile, the influence of patch length is rarely.Moreover, connect the orthogonal analysis result with the applied condition,the patch parameter is elected to repair the cracked metallic plate for the uniaxial tension test.And the test result indicates that the tension intensity of the repaired plate is 1.32 times than cracked plate,and 97.2% of the uncracked one, Meanwhile, the elongation of the repaired plate is 2.24 times than the unrepaired one,and 50.7% of the uncracked one.The repair effect is best when the square patch length is 40 mm, thickness is 1.2 mm and lay-up direction is [0°/90°]..
Key wordsAdhesively bonded composite repair,Finite element analysis,Orthogonal analysis,Contribution ratio,Tension test
0引言
我国军用飞机经过几十年的发展，飞机的老龄化收稿日期；201609-09；修回日期：20161230
问题也随之凸显。因此，老龄化飞机的延寿问题至关重要[1-2]。对于缺陷或损伤较大的结构，要及时进行
第一作者简介：穆志，1963年出生，教投，博士生导师，主要研究飞机结构寿命可靠性、虞蚀疫劳及离蚀控制。E-mail；mzt63@163.com 通信作者：牛勇，1987年出生，博士研究生，主要研究方向为金属损伤复合材料胶接修复。E-mail；niuyongshi@163.com
— 14 -万方数据
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2017年第3期