| 复合材料层压板抗冲击行为及表征方法的实验研究 |
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| 引用本文： | 沈真,杨胜春,陈普会. 复合材料层压板抗冲击行为及表征方法的实验研究[J]. 复合材料学报, 2008, 25(5): 125-133 |
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| 作者姓名： | 沈真 杨胜春 陈普会 |
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| 作者单位： | 1. 中国飞机强度研究所, 西安 710065;2. 南京航空航天大学, 南京 210016 |
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| 基金项目： | 国家自然科学基金（10742107）； 航空科学基金（04B23002） |
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| 摘 要： | 对14种复合材料体系约800个试样进行了冲击阻抗和含损伤层压板压缩强度试验研究，研究发现对于同一种复合材料层压板的冲击能量-凹坑深度曲线和凹坑深度-压缩破坏应变曲线均存在拐点，在出现拐点后内部的分层损伤叠加面积基本不再增加，压缩剩余强度基本不再降低，表面冲击部位开始出现纤维断裂。研究表明，采用传统CAI来表征损伤容限性能的方法可能得到与实际结构损伤容限特性相反的结论。因此，提出了利用拐点附近特性来表征复合材料层压板的抗冲击行为（包括损伤阻抗和损伤容限）的建议，即分别采用QSI方法得到的准各向同性层压板的最大接触力Fmax和压缩破坏强度（应变）的门槛值CAIT来表征复合材料层压板的损伤阻抗和损伤容限行为。
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| 关 键 词： | 复合材料层压板 冲击损伤 损伤阻抗 损伤容限 |
| 收稿时间： | 2007-11-22 |
| 修稿时间： | 2008-03-17 |
Experimental study on the behavior and characterization methods of composite laminates to withstand impact |
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| SHEN Zhen,YANG Shengchun,CHEN Puhui. Experimental study on the behavior and characterization methods of composite laminates to withstand impact[J]. Acta Materiae Compositae Sinica, 2008, 25(5): 125-133 |
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| Authors: | SHEN Zhen YANG Shengchun CHEN Puhui |
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| Affiliation: | 1. Aircraft Strength Research Institute of China, Xi'an 710065, China;2. Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China |
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| Abstract: | An experimental study on the impact resistance and compressive strength of damaged laminates was carried out by using about 800 specimens of 14 composite systems. It has been found that there is a common knee point for the impact energy-dent depth curve and the dent depth-compressive strength curve for the same type of composite laminates. The overlapped area of the inner delaminations does not increase and its compressive strength does not reduce generally after the knee point occurs. Some fiber breakage at the impact location on the surface could be visible after the knee point occurs. The damage tolerance behavior characterized by the traditional CAI method may get the opposite conclusion obtained from the structural verification test results. Therefore，a characterization system for damage tolerance and damage resistance behaviors of composite systems is proposed by using the knee point features of the capability of composite laminates to withstand impact (including damage resistance and damage tolerance)，i.e. the damage resistance and damage tolerance behavior is characterized by means of the maximum contact force，Fmaxand the compressive failure threshold value (strength or failure strain) (CAIT) of the specimens with quasi-isotropic stacking sequence respectively. |
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| Keywords: | composite laminates impact damage damage resistance damage tolerance |
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