摘要
采用材料弹性系数的刚度退化模型分析了复合材料挖补结构的极限强度。基于Mayes模型提出了一种复合材料层合板的刚度退化方法,以带中心孔拉伸试件为对象,在完成有限元网格划分与单元选取的适应性研究后,使用复合材料层压板挖补试验件进行了渐进损伤分析方法的有效性验证。开展了挖补结构的渐进损伤分析和挖补参数对极限强度的影响研究。研究结果表明,采用层合单元的有限元模型和基于材料弹性系数的刚度退化模型,可以作为复合材料修补结构强度的基本分析模型,计算效率和分析精度能够满足工程分析需求,修补设计参数对修补结构强度的影响呈非线性。研究结果可以为复合材料层压板挖补修理设计提供参考。
A stiffness degeneracy reduction analysis method based on Mayes model for composite laminates is presented in this paper. The most carrying capacity of the composite laminates with scarf repaired is analyzed. After establishing method studied of FEMmodel of a tension test specimen with a hole in the center,testing results of two kinds of repaired composite laminate specimens ars used for certification method. The predicted results are consistent with the experimental results which means the model can predict the carrying capacity. The damage evolution process and influence of patch parameters on the tensile behavior of repaired structures are also studied. The study results indicate that the progressive damage analysis method based on reduction of material elastic parameter can be used for strength analysis of repaired composite structure. The strength increase is not alike in different failure modes when patch parameters change. Results of study can provide some reference for the repair design for composite laminates.
作者
宋恩鹏
洪海明
张音旋
周丽
SONG En-peng HONG Hai-ming ZHANG Yin-xuan ZHOU Li(Shenyang Aircraft Design ＆ Research Institute, Shenyang 110035, China State Key Laboratory of Mechanics and Control of Mechanical Structures, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China)
出处
《飞机设计》
2017年第4期28-31,36,共5页
Aircraft Design
关键词
复合材料
修理
渐进损伤
分析
composite
repair
progressive damage
analysis
