复合材料开孔板拉伸损伤对剩余压缩强度的影响
Effect of tension damage on structures residual compression strength of open-hole composite laminates
王湘江 1夏俊康 1冀运东 2曹东风 3胡海晓 4李书欣5
作者信息
- 1. 武汉理工大学 新材料力学理论与应用湖北省重点实验室,武汉 430070;武汉理工大学 材料复合新技术国家重点实验室,武汉 430070
- 2. 武汉理工大学 材料复合新技术国家重点实验室,武汉 430070
- 3. 武汉理工大学 材料复合新技术国家重点实验室,武汉 430070;先进能源科学与技术广东省实验室佛山分中心(佛山仙湖实验室),佛山 528000;武汉理工大学先进材料制造装备与技术研究院,武汉 430070
- 4. 武汉理工大学 新材料力学理论与应用湖北省重点实验室,武汉 430070;先进能源科学与技术广东省实验室佛山分中心(佛山仙湖实验室),佛山 528000;武汉理工大学先进材料制造装备与技术研究院,武汉 430070
- 5. 武汉理工大学 新材料力学理论与应用湖北省重点实验室,武汉 430070;武汉理工大学 材料复合新技术国家重点实验室,武汉 430070;先进能源科学与技术广东省实验室佛山分中心(佛山仙湖实验室),佛山 528000;武汉理工大学先进材料制造装备与技术研究院,武汉 430070
- 折叠
摘要
通过试验和数值分析相结合的方式,探究含孔复合材料层合板拉伸损伤对其剩余压缩强度和失效模式的影响.试验方面,首先,通过开孔复合材料层合板拉伸试验引入两种程度的拉伸损伤,使用热揭层方法表征和量化其拉伸损伤程度.随后,开展含拉伸损伤的开孔复合材料层合板压缩试验,记录其载荷-位移曲线,并通过数字图像相关法(DIC)、应变片、微距相机等手段观察其变形和损伤演化特征.数值分析方面,构建基于LaRC失效准则的渐进损伤失效模型描述层内损伤演化,使用内聚力单元方法刻画复合材料层间分层损伤,基于此模型探究了开孔复合材料层合板损伤扩展规律.试验结果表明:拉伸载荷引起的孔边复合材料损伤以基体裂纹和分层损伤为主,在加载方向和纤维朝向夹角较小的层间,分层损伤程度更大.拉伸损伤会进一步加剧孔周应变集中,使孔邻域应变呈非对称,导致结构局部屈曲更早地发生,进而诱发结构整体破坏,相对于不含拉伸损伤开孔板,含拉伸损伤开孔板可使结构压缩承载能力下降 25.8%.构建的数值计算模型可以准确预测拉伸载荷下孔周剪切应力引起的分层损伤和压缩阶段应变域场演化特征,也可揭示含不同程度拉伸损伤的开孔板压缩损伤扩展模式差异及探究纤维弯折失效、基体损伤和层间分层对结构承载能力的影响规律,为复合材料开孔板在变载荷作用下结构设计与剩余强度的确定提供支撑.
Abstract
The influence of tension damage on residual compression strength and failure mode of open-hole com-posite laminates was investigated by tests and numerical analysis.In terms of test,firstly,two degrees of tension damage were introduced through the tension test of open-hole composite laminates,and the degree of tension damage was characterized and quantified by the thermal decal method.Then,the compression test of open-hole composite laminates with tension damage was carried out,the load-displacement curve was recorded.The damage evolution characteristics were observed by digital imaging correlation(DIC),strain gauge,macro camera and other means.In terms of numerical analysis,a progressive damage failure model based on LaRC failure criteria was con-structed to describe the intralaminar damage evolution,and cohesive elements method was established to describe the interlaminar damage of composite materials.Based on this model,the damage expansion law of open-hole composite laminates was explored.The experimental results show that the damage caused by tensile load is mainly matrix crack and delamination damage,and the delamination damage is greater between layers with small angle between loading direction and fiber direction.Tension damage will further aggravate the strain concentration around the hole,resulting in an asymmetric strain in the neighboring region of the hole,leading to the local buck-ling of the structure earlier,and then inducing the overall failure of the structure.Compared with the open-hole composite laminates without tension damage,the open-hole composite laminates with tension damage can reduce the compressive bearing capacity of the structure by 25.8%.The constructed numerical calculation model can accurately predict the delamination damage caused by the shear stress around the hole under tensile load and the evolution characteristics of the strain field in the compression stage,and can also reveal the difference in the com-pression damage expansion mode of the open-hole composite laminates with different degrees of tension damage,and explore the effects of fiber bending failure,matrix damage and interlayer delamination on the structural bear-ing capacity.This work can provide support for structural design and determination of residual strength of open-hole composite laminates under varying loading.
关键词
含孔复合材料层合板/剩余压缩强度/LaRC失效准则/渐进损伤/变载荷Key words
open-hole composite laminates/residual compression strength/LaRC failure criteria/progressive damage/variable loading引用本文复制引用
基金项目
国家自然科学基金(52273080)
国家自然科学基金(12202325)
中央高校基本科研业务费专项(WUT2021IVA068)
出版年
2024
NETL
NSTL
万方数据