| 引用本文: | 王新筑,周雄,朱炳杰,等.金属泡沫复合材料夹芯结构的压痕响应实验.[J].国防科技大学学报,2017,39(1):189-193.[点击复制] |
| WANG Xinzhu,ZHOU Xiong,ZHU Bingjie,et al.Indentation experiment of composite sandwich structure with metal foam core[J].Journal of National University of Defense Technology,2017,39(1):189-193[点击复制] |
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| 金属泡沫复合材料夹芯结构的压痕响应实验 |
| 王新筑1,2,3, 周雄4, 朱炳杰5, 彭向和4 |
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(1. 吉林大学 汽车仿真与控制国家重点实验室， 吉林 长春 130025;2.
2. 湖南大学 汽车车身先进设计制造国家重点实验室， 湖南 长沙 410082;3.
3. 重庆大学 航空航天学院 非均质材料力学重庆市重点实验室， 重庆 400040;4.3. 重庆大学 航空航天学院 非均质材料力学重庆市重点实验室， 重庆 400040;5.4. 国防科技大学 航天科学与工程学院， 湖南 长沙 410073)
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| 摘要: |
| 金属泡沫夹芯结构是近年来新出现的一种明显具有结构和功能一体化特点的新型轻质材料，它在临近空间飞行器、航海及汽车等领域有着广阔的应用前景。以以纤维增强复合材料面板、闭孔泡沫铝芯子为特征的复合材料夹芯结构为研究对象，对其在球形压头作用下的压痕响应、损伤模式、变形机制和失效机理进行理论分析和实验研究。研究发现，泡沫铝复合材料夹芯结构的压痕响应是夹芯结构的各个组成部分的响应、相互作用以及压头属性的综合作用结果。泡沫铝复合材料夹芯结构在球压头作用下的损伤模式为基体开裂、纤维断裂、层间分层、泡沫铝的屈服及剪切断裂五种失效模式。 |
| 关键词: 金属泡沫 夹芯结构 压痕响应 损伤模式 失效机理 |
| DOI：10.11887/j.cn.201701029 |
| 投稿日期：2015-05-28 |
| 基金项目:汽车仿真与控制国家重点实验室开放基金资助项目(20121110)；汽车车身先进设计制造国家重点实验室开放基金资助项目(31315010)；中央高校基本科研业务费资助项目(CDJZR14325501)；中国博士后基金面上资助项目(2011M500067) |
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| Indentation experiment of composite sandwich structure with metal foam core |
| WANG Xinzhu1,2,3, ZHOU Xiong4, ZHU Bingjie5, PENG Xianghe4 |
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(1. State Key Laboratory of Automotive Simulation and Control， Jilin University， Changchun 130025， China;2.
2. State Key Laboratory of Advanced Design and Manufacture for Vehicle Body, Hunan University, Changsha 410082, China;3.
3. Chongqing Key Laboratory of Heterogeneous Material Mechanics, College of Aerospace Engineering, Chongqing University, Chongqing 400040, China;4.3. Chongqing Key Laboratory of Heterogeneous Material Mechanics, College of Aerospace Engineering, Chongqing University, Chongqing 400040, China;5.4. College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China)
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| Abstract: |
| Sandwich structure with metal foam core is a newly emerged sandwich structure in recent years, and will be widely used in near space flight vehicle, navigation and automobile fields due to its high flexural rigidity and strength, multifunction. Theoretical analysis and experimental studies on the indentation response, damage modes, deformation mechanism and failure mechanism of the composite sandwich panel with fibre-reinforced polymer face and aluminum foam core under the action of rigid spherical-end indenter were conducted. Study results show that the load-indentation response is a combined consequence of the individual responses of the sandwich components, their structural interactions and the indenter properties. The failure models of the sandwich panel under the spherical-end cylindrical indenter can be summarized as matrix cracking, fiber fracture, face/core debonding, the yield and shear of the aluminum foam. |
| Keywords: metal foam sandwich structure indentation damage mode failure mechanism |
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