摘要
基于累积损伤理论对金属-复合材料单钉连接件强度和刚度进行研究。分析层合板钉孔挤压损伤后剩余刚度的变化规律,提出在挤压变形和强度计算中,针对基体和纤维压缩失效,采用相关模量先突减、然后逐渐提升的刚度修正方法。分析获得钉-孔挤压区基体和纤维压缩失效后的材料刚度(模量)参数随压缩应变量变化的规律,用来模拟连接结构的挤压强度和刚度行为,与试验结果相吻合。
Mechanical strength of single-bolted composite joints was investigated using cumulative damage technique. Aware that the residual bearing stiffness of a joint may vary after the occurrence of pin-hole bearing damage. The stiffness modification technique put forward in this paper states that the moduli of the material related to fiber and matrix compression failure in bearing zone are subjected to a sudden drop and then raising gradually. The results to apply the laws of material properties （modulus） vary with the compressive strains after matrix and fiber compression failure in pin-hole bearing area attained to predict joint strength and stiffness behavior, are just in good agreement with the test results.
出处
《航空材料学报》
EI
CAS
CSCD
北大核心
2014年第5期81-87,共7页
Journal of Aeronautical Materials
基金
航空科学基金(20120953010)
关键词
复合材料层合板
机械连接
累积损伤
刚度修正
composite laminate
mechanical joint
cumulative damage
stiffness modification
