摘要
对T700/9368光滑板及两种孔径的含孔层合板进行了拉-拉疲劳试验,测量试件刚度随加载周期的衰减规律,并利用超声波C扫描和破坏断口分析方法,对T700复合材料的疲劳损伤机理进行分析。根据弹性模量法建立了层合板疲劳累积损伤模型,并从平均应力准则概念出发,建立了含孔层合板的疲劳累积损伤模型。将试验数据运用最小二乘法拟合后代入疲劳损伤模型,得到T700/9368光滑板及含孔板疲劳寿命的具体计算公式,应用公式预测了在不同应力水平下的层合板疲劳寿命,与试验结果的吻合良好。
Tension-tension fatigue test was carried out on T700/9368 composite smooth laminates and those with a hole of different di- ameter. The stiffness attenuation of the specimens was measured while bearing fatigue load and the fatigue damage mechanism of T700/ 9368 composite laminates was explored by ultrasonic C-scan. The damage model of the laminates was established according to the ＂Means of Elasticity Modulus＂. Based on average stress criterion, the damage model of the laminates with holes was established as well. The experimental data was fit into the fatigue damage model with least-squares method, to obtain a specific formula for calculating the fatigue life of T700/9368 laminates. Applying this formula to predict fatigue life of laminates under several different stress levels, the results are in a good agreement with experimental data.
出处
《航空材料学报》
EI
CAS
CSCD
北大核心
2012年第3期85-90,共6页
Journal of Aeronautical Materials
基金
北京航空航天大学凡舟科研基金(20060504)
