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胶接修补复合材料层合板失效分析的PDA-CZM方法
引用本文:林国伟,陈普会.胶接修补复合材料层合板失效分析的PDA-CZM方法[J].航空学报,2009,30(10):1877-1882.
作者姓名:林国伟  陈普会
作者单位:南京航空航天大学,飞行器先进设计技术国防重点学科实验室,江苏,南京,210016
摘    要: 建立了一种预测胶接修补复合材料层合板的损伤演变与剩余强度的PDA-CZM方法。该方法应用三维渐进损伤分析(PDA)方法和粘聚区模型(CZM)分别模拟复合材料层合板和修补胶层的失效过程。对修补层合板的纤维断裂、基体开裂、层间分层以及胶层脱胶等损伤的萌生和扩展以及它们之间的耦合作用进行了研究。计算得到了修补结构的载荷--位移曲线,并预测了其极限强度。计算结果和试验数据吻合良好,验证了PDA-CZM方法的有效性。最后,讨论了修补参数对剩余强度的影响规律。

关 键 词:层合板  修补  损伤  粘聚区模型  分层  

PDA-CZM Method for Failure Analysis of Bonded Repair of Composite Laminates
Lin Guowei,Chen Puhui.PDA-CZM Method for Failure Analysis of Bonded Repair of Composite Laminates[J].Acta Aeronautica et Astronautica Sinica,2009,30(10):1877-1882.
Authors:Lin Guowei  Chen Puhui
Institution:Defense Key Disciplines Laboratory for Aircraft Design, Nanjing University of Aeronautics and Astronautics
Abstract:A novel method (PDA-CZM method) is proposed to predict the damage evolution and residual strength of laminated composites bonded with composite patches. The three-dimensional progressive damage analysis (PDA) and the cohesive zone model (CZM) are used to simulate respectively the damage progression in laminated composites and that in the adhesive layer. The initiation and propagation of fibre damage, matrix cracking, delamination,and adhesive failure of repaired composite laminates as well as the coupling effect among them is investigated. Load-displacement curves and ultimate strengths are obtained by numerical analysis. An excellent agreement is found between the numerical results and the test data, and the validity of the analysis method is proved. Finally, the effect of repair parameters on the residual strength of the repaired laminated composites is discussed.
Keywords:laminated composite  repair  damage  cohesive zone model  delamination
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