Experimental investigation of large-scale high-velocity soft-body impact on composite laminates
Experimental investigation of large-scale high-velocity soft-body impact on composite laminates
复制标题
复合材料层合板大规模高速软体冲击实验研究
DOI：
10.1016/j.ijimpeng.2021.104089
复制
发表时间：
2022
影响因子：
5.1
通讯作者：
Cochrane A
中科院分区：
文献类型：
--
作者：
Cochrane A
由碳纤维预浸料制成的高性能航空航天层压复合材料结构在飞行冲击条件下非常容易出现分层失效。在小长度尺度和准静态应变率下进行了大量测试，以表征不同材料系统和加载场景的分层性能。这种规模和应变率的测试并不能代表层压板在真实冲击事件中经历的失效情况。还进行了全面测试，但由于知识产权限制，其中大部分内容并未公开。这种规模的测试也非常昂贵，并且涉及复杂的故障机制，导致难以分析相关的故障行为。提出了一种新颖的测试，它为全面测试提供了一种简单、经济的替代方案，但它以足够的规模和速度调用故障来代表真实的组件故障。该测试设计通过使用轻型气枪设施的一系列软体明胶冲击测试进行了实验验证。使用扫描电子显微镜进行断口分析，以检查微观失效行为，显示裂纹扩展过程中裂纹模式比可能降低。
High-performance aerospace laminated composite structures manufactured from carbon-fibre prepreg are very susceptible to delamination failure under in-flight impact conditions. Much testing has been conducted at small length scales and quasi-static strain-rates to characterise the delamination performance of different material systems and loading scenarios. Testing at this scale and strain-rate is not representative of the failure conditions experienced by a laminate in a real impact event. Full-scale testing has also been conducted, but much of this is not in the open literature due to intellectual property constraints. Testing at this scale is also prohibitively expensive and involves complex failure mechanisms that cause difficulty in the analysis of associated failure behaviour. A novel test is presented which provides a simple, affordable alternative to full-scale testing but which invokes failure at sufficient scale and velocity to be representative of real component failure. This test design is experimentally validated through a series of soft-body gelatine impact tests using a light gas-gun facility. A fractographic analysis using scanning-electron microscopy was undertaken to examine microscopic failure behaviour, showing a possible reduction in crack mode-ratio during propagation.