含表面划伤平纹编织面板蜂窝夹芯结构侧向压缩渐进失效分析

玻璃钢/复合材料 ›› 2019, Vol. 0 ›› Issue (7): 5-10.

• 基础研究 • 下一篇

含表面划伤平纹编织面板蜂窝夹芯结构侧向压缩渐进失效分析

周春苹¹, 刘武帅², 王轩², 曹阳丽²

1.航空工业济南特种结构研究所高性能电磁窗航空科技重点实验室,济南250023;
2.中国民航大学航空工程学院,天津300300

收稿日期:2019-04-12 出版日期:2019-07-28 发布日期:2019-07-28
作者简介:周春苹(1981-),女,硕士,高级工程师,主要从事复合材料结构强度计算和试验方面的研究,zcp99241@126.com。
基金资助:
国家自然科学基金(11702317);航空科学基金(高性能电磁窗航空科技重点实验室资助)(20151867004);中国民航大学中央高校基本科研业务费项目(3122015C007)

STUDY ON EDGEWISE COMPRESSION PERFORMANCE OF HONEYCOMB SANDWICH STRUCTURE WITH SCRATCH DAMAGE

ZHOU Chun-ping¹, LIU Wu-shuai², WANG Xuan², CAO Yang-li²

1.Aviation Key Lab of Science and Technology on High Performance Electromagnetic Windows, Research Institute for Special Structure of Aeronautical Composite, AVIC, Jinan 250023, China;
2.College of Aeronautical Engineering, Civil Aviation University of China, Tianjin 300300, China

Received:2019-04-12 Online:2019-07-28 Published:2019-07-28

摘要/Abstract

摘要： 为研究表面划伤对平纹编织面板蜂窝夹芯结构侧压性能的影响,建立平纹编织面板蜂窝夹芯结构的渐进失效分析模型。考虑模型具有高度的材料非线性问题,选用ABAQUS/Explicit求解器进行蜂窝夹芯结构的准静态侧向压缩模拟,通过编写VUMAT子程序,分别设置面板和芯子的失效准则以及刚度退化模型,选用内聚力模型模拟胶层,完成含表面划伤的平纹编织面板蜂窝夹芯结构的侧向压缩渐进失效分析,与试验结果相比,破坏强度和失效模式非常吻合。研究结果表明:失效时无损伤一侧面板会产生屈曲行为,使得蜂窝芯面外应力增大,导致蜂窝芯出现损伤。含表面划伤一侧面板会发生经向纤维压缩失效及纤维-基体经向剪切失效,且失效会沿划伤方向从划伤区域附近向两侧扩展。

关键词: 蜂窝夹芯结构, 渐进失效模型, VUMAT子程序, 划伤, 侧压强度

Abstract: The progressive damage analysis model of honeycomb sandwich structure with plain braided panel is established. The lateral strength and failure mode of honeycomb sandwich structure with scratch damage on one side panel are studied. The results are compared with the experiments to verify the correctness of the model. Considering the high material nonlinearity of the model, ABAQUS/Explicit solver is used to simulate the quasi-static lateral compression of honeycomb sandwich structure. By compiling VUMAT subroutine, failure criteria and stiffness degradation models of panel and core are set respectively, and cohesion model is used to simulate the adhesive layer to complete progressive damage analysis of honeycomb sandwich structure subjected to lateral compression. The results show that the buckling behavior of the unilateral plate without damage will occur when the failure occurs, which will increase the stress outside the honeycomb core surface and lead to the damage of the honeycomb core. The longitudinal compression failure of fiber and the longitudinal shear failure of the fiber-matrix will occur on one side plate with surface scratches, and the failure will extend from the vicinity of the scratch area to both sides along the scratch direction.

Key words: plain weave honeycomb sandwich structure, progressive damage model, VUMAT subroutine, scratch, edgewise compressive strength

中图分类号:

TB332

周春苹, 刘武帅, 王轩, 曹阳丽. 含表面划伤平纹编织面板蜂窝夹芯结构侧向压缩渐进失效分析[J]. 玻璃钢/复合材料, 2019, 0(7): 5-10.

ZHOU Chun-ping, LIU Wu-shuai, WANG Xuan, CAO Yang-li. STUDY ON EDGEWISE COMPRESSION PERFORMANCE OF HONEYCOMB SANDWICH STRUCTURE WITH SCRATCH DAMAGE[J]. Fiber Reinforced Plastics/Composites, 2019, 0(7): 5-10.

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含表面划伤平纹编织面板蜂窝夹芯结构侧向压缩渐进失效分析

STUDY ON EDGEWISE COMPRESSION PERFORMANCE OF HONEYCOMB SANDWICH STRUCTURE WITH SCRATCH DAMAGE

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