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作 者:邹雄辉 高维成[1] 刘伟[1] 周睿 ZOU Xionghui;GAO Weicheng;LIU Wei;ZHOU Rui(School of Astronautics,Harbin Institute of Technology,Harbin 150001,China)
出 处:《材料导报》2022年第24期191-197,共7页Materials Reports
摘 要:复合材料工型梁是飞机舱门结构中的重要承力部件,其在压缩载荷下的失稳行为和损伤特性是工程设计中关注的要点。为了研究复合材料工型梁的压缩性能和失效模式,开展了轴向压缩试验和数值仿真计算。选取改进的Hashin准则判定层内损伤,引入内聚力胶层单元模拟层间损伤,并采用一种新的基于复合材料破坏现象的刚度退化模型对材料的性能进行折减。在模型中综合考虑了纤维扭折和翼缘侧向支撑作用对材料性能压缩失效的影响。计算得到的载荷-位移曲线、载荷-应变曲线、破坏模式以及破坏载荷均与试验结果符合较好,验证了模型的准确性。基于经试验验证后的模型,对工型梁截面进行了参数化分析,研究了长宽比、翼缘宽厚比对复合材料工型梁屈曲性能和承载能力的影响规律,为实际工程结构优化及选型提供了参考。Composite I-beam is an essential load-bearing component in aircraft structure,and its instability behavior and damage characteristics under compressive load are the key points in engineering design.In order to study the compression performance and failure modes of composite I-beams,axial compression tests and numerical simulation calculations were carried out.The improved Hashin criterion was selected to determine the intra-layer damage,the cohesive adhesive element was introduced to simulate the inter-layer damage,and a stiffness degradation model based on the failure phenomenon of composite materials was used to reduce the material stiffness.In the model,the effects of fiber deflection and flange lateral support on the material performance after compression failure were comprehensively considered.The calculated load-displacement curve,load-strain curve,failure mode and failure load are in good agreement with the test results,which verifies the accuracy of the finite element model.Based on the experimentally verified model,a parametric analysis of the I-beam section was carried out,and the influence of the aspect ratio and flange width-thickness ratio on the buckling performance and bearing capacity of the composite I-beam was investigated,providing a reference for engineering structure optimization and selection.
关 键 词:复合材料工型梁 压缩试验 失效 分层损伤 截面参数
分 类 号:TB332[一般工业技术—材料科学与工程]
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