航空复合材料纸蜂窝夹芯结构热成型开裂研究  

Research on the crack of thermo-forming of aviation sandwich structure composed of composite materials and paper honeycomb

作　　者：蔡豫晋 徐伟伟 文友谊 向栋 李博 宋志梅 刘斌[2] 徐绯[2] CAI Yujin;XU Weiwei;WEN Youyi;XIANG Dong;LI Bo;SONG Zhimei;LIU Bin;XU Fei(Chengdu Aircraft Industrial(Group)Co.,Ltd.,Chengdu 610092,China;School of Aeronautics,Northwestern Polytechnical University,Xi’an 710072,China)

机构地区：[1]成都飞机工业(集团)有限责任公司,成都610092 [2]西北工业大学航空学院,西安710072

出　　处：《航空工程进展》2023年第2期97-104,共8页Advances in Aeronautical Science and Engineering

基　　金：国家自然科学基金(51902256);航空科学基金(2020Z057053002)。

摘　　要：飞机复合材料芳纶纸蜂窝夹芯部件在热压罐成型时处于热—力耦合工况,在热成型过程中可能出现蜂窝开裂现象。通过试验获得蜂窝芯的拉、压、剪性能参数和芳纶纸的热性能参数,结合有限元分析和反演方法,对整体蜂窝夹芯部件的热—力顺序耦合和局部芯子抽真空导致的蜂窝胞元间压强差进行数值模拟。结果表明:成型过程中的热应力不会导致蜂窝胞元间胶层开裂,局部憋气的压强差可能导致蜂窝开裂;胶层部分破坏与胶层完全破坏所需的胞元间压强差的差值与胶层初始法向断裂应力正相关;胶层完全破坏所需的胞元间压强差随着受载胞元数量的增多而减小。During the forming of aramid paper honeycomb sandwich component of aircraft composites in the autoclave,the structure bears thermo-mechanical coupling case,and it may exist the phenomenon of the honeycomb crack during the forming.The tensile,compressive,shear and thermal properties of aramid paper honeycomb core are obtained by testing.Meanwhile,the numerical simulation of thermo-mechanical sequential coupling of the whole honeycomb sandwich component and the local core area are carried out by combining the finite element analysis method and the inversion method.The results show that the thermal stress during the forming process will not cause the adhesive layer between honeycomb cells to crack,but gas pressure will.The difference value of pressure difference between honeycomb cells required for adhesive layer's slight destruction and complete destruction is positively related to the initial normal fracture stress of adhesive layer.The pressure difference required for the adhesive layer's complete destruction is decreased with the increase of the number of loaded cells.

关 键 词：蜂窝夹芯结构 热成型 开裂 有限元分析 内聚力单元 

分 类 号：V214.5[航空宇航科学与技术—航空宇航推进理论与工程]