陈亚军.复合材料加筋壁板长桁蒙皮剥离失效分析[J].民用飞机设计与研究,2018,(2):59-
复合材料加筋壁板长桁蒙皮剥离失效分析
Numerical Study on Peeling Failure of Stiffened Composite Panel
  
DOI:10.19416/j.cnki.1674-9804.2018.02.011
中文关键词:复合材料加筋壁板  面内损伤  cohesive单元  脱胶  剥离
英文关键词:stiffened composite panel  interlaminar damage  cohesive element  debonding  peeling
基金项目:
作者单位
陈亚军 上海飞机设计研究院上海201210 
中文摘要:为了研究复合材料加筋壁板在纯弯载荷作用下蒙皮与长桁间的脱胶过程,基于ABAQUS有限元软件中的连续壳单元和Cohesive单元建立了有限元模型。在该模型中,采用Hashin准则预测面内损伤,而对于蒙皮与长桁缘条之间脱胶损伤的起始与扩展,则采用Cohesive单元进行模拟。采用该模型对复合材料加筋壁板蒙皮与长桁在纯弯载荷作用下的破坏过程进行仿真,仿真结果与试验结果相比较表明,本文建立的有限元分析模型能较好地模拟加筋壁板在纯弯载荷作用下蒙皮与长桁间的脱胶过程,并且能较好地预测该结构的剥离强度。
英文摘要:This paper presents the results of numerical investigation concerning peeling failure of stiffened composite panel under pure bending. A finite element model which consists of continuous shell elements and cohesive elements is developed using ABAQUS finite element code. In the model, Hashin criterion is used to determine the interlaminar damage; and the debonding between skin and stringer flange is simulated via cohesive elements. Failure of stiffened composite panel under pure bending is investigated. Some conclusions are obtained based on the results. The finite element model is so useful that the peeling load and peeling strength of stiffened composite panel can be well predicted.
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