摘要
复合材料在航空领域的应用越来越广泛,在对其具有强大需求的背景下,如何通过理论与试验更好地预测其关键部位性能,也变得极为重要。目前金属-复合材料连接行为仍是一个难点,现有航空结构的关键部位还需金属连接,这就有必要进行金属-复合材料连接研究。本文通过考虑树脂基复合材料的固化残余应力,针对积木式试验中的元件级别,采用通用有限元软件ANSYS对双向金属-复合材料元件的力学行为响应进行数值模拟研究。计算结果表明:元件级别的金属-复合材料连接部分固化残余变形高达0.67 mm,主要表现为翘曲变形。在极限应变下,层间应变高达0.022 mm。
Composite is widely used in the aviation industry. It＇s very important to predict the performance of the critical region by analysis or experiment. Even in the modern aircraft structures metallic joint are needed, and the analysis of the hybrid structures is a key problem. During the elements level of ＂ Building Block＂ tests, we analyzed the hybrid joint of composite - metal structures by ANSYS finite element software. In the model, we calculated the biaxial tension behavior of the joint, and taken into account the residual curing stress of composite parts. It is found that the specimen warped, and the residual curing stress of the joint region is 0.67 mm. When the structure is under ultimate strain, the interlaminar strain is 0.022 mm.
出处
《纤维复合材料》
CAS
2013年第2期18-22,共5页
Fiber Composites
