【作者】 林国伟；

【导师】 陈普会；

【作者基本信息】 南京航空航天大学 ， 飞行器设计， 2009， 硕士

【摘要】 复合材料结构的胶接修补研究是当前复合材料结构完整性评定中亟待解决的核心问题之一。本文在前人的工作基础上主要开展了以下几方面的研究工作:1、针对胶接修补中的挖补修理方式,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理论(PDA)和内聚力模型(CZM)分别模拟复合材料层合板和修补胶层的失效过程。对该方法作了详细介绍。2、对楔形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,并预测了修补结构的极限强度。计算结果和试验数据吻合良好,验证了PDA-CZM方法的有效性。3、详细探讨了挖补角度、胶层厚度等参数对楔形修补强度的影响规律,给出了最佳的修补方案,用来指导实际的修补工作。4、对阶梯挖补的复合材料层合板失效过程和承载能力进行分析,以及对目前工程中常见的两种挖补方式即楔形挖补和阶梯挖补进行分析比较,得出了一些有实用价值的结论。更多还原

【Abstract】 Study of laminated composites bonded with composite patch is key problem to be solved in order to assess composite structure integrality. The main contents of this paper are summarized as below:1、This paper mainly discusses the scarf patch repair of composites. A novel method is proposed to predict damage evolution and residual strength of laminated composites bonded with composite patch. The three-dimensional progressive damage analysis (PDA) and the cohesive zone model (CZM) are used to simulate damage progression in laminated composites and adhesive layer respectively. This predictive method is introduced detailedly.2、The initiation and propagation of fibre damage, matrix cracking, delamination and adhesive failure of repaired composite laminates as well as coupling effect among them is investigated. Load-displacement curve and ultimate strength are obtained by numerical analysis. An excellent agreement is found between the numerical results and the test data, and the validity of analysis method is proved.3、The effect of repair parameters, such as the scarf angle, thickness of the adhesive, etc. on the strength of repaired structures are discussed in detail. The best repair methods are obtained to instruct actual repair work.4、The strength and failure process of stepped patch repair composites are simulated. Stepped patch repair method is also compared with scarf patch repair method, and some useful conclusions are captured.更多还原