航空学报 > 2009, Vol. 30 Issue (10): 1877-1882

胶接修补复合材料层合板失效分析的PDA-CZM方法

林国伟,陈普会   

  1. 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
  • 收稿日期:2008-09-02 修回日期:2009-01-06 出版日期:2009-10-25 发布日期:2009-10-25
  • 通讯作者: 陈普会

PDA-CZM Method for Failure Analysis of Bonded Repair of Composite Laminates

Lin Guowei, Chen Puhui   

  1. Defense Key Disciplines Laboratory for Aircraft Design, Nanjing University of Aeronautics and Astronautics
  • Received:2008-09-02 Revised:2009-01-06 Online:2009-10-25 Published:2009-10-25
  • Contact: Chen Puhui

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

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.

Key words: laminated composite, repair, damage, cohesive zone model, delamination

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