摘要
建立平纹编织面板蜂窝夹芯结构的渐进损伤分析模型来分别研究无损伤面板和单侧面板含穿孔损伤的蜂窝夹芯结构的侧向压缩性能,并将该结果与试验结果进行对照,以验证所建立模型的正确性。考虑到模型具有高度的材料非线性,选用ABAQUS/Explicit求解器进行蜂窝夹芯结构准静态侧向压缩性能的模拟,通过编写VUMAT子程序,分别设置面板和芯子的失效准则及刚度退化模型,选用内聚力模型模拟胶层,完成侧向压缩下蜂窝夹芯结构的渐进损伤分析。研究结果表明:无损伤面板的蜂窝夹芯结构侧向压缩强度受面板的屈曲行为控制,含穿孔损伤的蜂窝夹芯结构侧向压缩强度受含穿孔侧面板基体的抗压缩能力控制,且穿孔损伤会严重降低蜂窝夹芯结构的侧向压缩强度。
A progressive damage model of honeycomb sandwich structures with plain woven panels was established to study the edgewise compressive performances of honeycomb sandwich structures with no-damage panels and with perforation damages on single side panels respectively, and the results were compared with the testing results to verify the correctness of the model. Considering the high material nonlinearity of the model, ABAQUS/Explicit solver was used to simulate the quasi-static edgewise compressive performances of honeycomb sandwich structures. By compiling VUMAT subroutine, failure criteria and stiffness degradation model of the panels and cores were set up respectively. Cohesive model was used to simulate the adhesive and progressive damage analyses of honeycomb sandwich structures subjected to edgewise compression were simulated. The research results show that the edgewise compressive strengths of honeycomb sandwich structures with no-damage panels are controlled by the buckling behaviors of the panels, and the edgewise compressive strengths of honeycomb sandwich structures with perforation damages on single side panels are controlled by the compression resistances of the panel matrixes with perforation, as well as the perforation damages may seriously reduce the edgewise compressive strengths of honeycomb sandwich structures.
作者
王轩
刘武帅
余芬
邓云飞
周春苹
WANG Xuan;LIU Wushuai;YU Fen;DENG Yunfei;ZHOU Chunping(College of Aeronautical Engineering, Civil Aviation University of China,Tianjin,300300;Aviation Key Lab of Science and Technology on High Performance Electromagnetic Windows,AVIC Research Institute for Special Structure of Aeronautical Composite,Jinan,250023)
出处
《中国机械工程》
EI
CAS
CSCD
北大核心
2019年第17期2076-2083,共8页
China Mechanical Engineering
基金
国家自然科学基金资助项目(1170020537)
航空科学基金资助项目(20151867004)
关键词
平纹编织面板蜂窝夹芯结构
渐进损伤分析模型
穿孔
侧向压缩强度
honeycomb sandwich structure with plain woven panel
progressive damage analysis model
perforation
edgewise compressive strength
