受载复合材料角片弯角区域应力分布特征分析  

Stress Analysis of Composite Curved Laminate Under Loading

作　　者：黄豪杰[1] 张俊琪[2] 刘龙权[2] 汪海[2] 

机构地区：[1]上海飞机设计研究院,上海201210 [2]上海交通大学航空航天学院,上海200240

出　　处：《上海交通大学学报》2014年第8期1116-1121,共6页Journal of Shanghai Jiaotong University

摘　　要：为了分析受载复合材料角片在弯角区域的应力分布特征,建立了受载复合材料弯角的有限元模型.通过对一组复合材料弯角结构进行准静态拉伸试验,并通过对比载荷-位移曲线、载荷-应变曲线、失效模式和失效位置等力学响应,验证了有限元模型的正确性.应用所建模型,分析了复合材料角片弯角区域沿轴向、径向和宽度方向的应力分布特征,以及角片厚度对弯角区域应力分布特征的影响.结果发现:受载复合材料角片的主要失效模式是弯角区域分层,受载时材料内部面外剪应力相对较低,分层主要受面外正应力影响;对于所分析的14层复合材料角片,分层起始位置沿径向比较靠近内部圆角处、沿周向位于29°处、沿宽度方向位于中面处;随角片厚度的增加,其承载能力提高;角片越厚,在厚度方向上分层起始位置从绝对距离上说越远离内角,但是此分层起始位置至内角的距离与板厚的比值越小;角片越厚,其分层起始位置越靠近加载端.To study the stress distribution of curved composite laminate under loading,agroup of specimens were quasi-staticly tested by using displacement control method.The finite element model of curved laminate was constructed by commercial finite element software ABAQUS,and the numerical model was validated through comparing with the test results.By analyzing the stress distribution under different load conditions,the following conclusions can be drawn：the main failure mode of the curved laminates under loading is delmination,and theσ33dominates the cause of the delamination;the onset of the delamination is close to the inner surface of the curved region along the radial direction,at about 29°along the circumferential direction,on the symmetric plane along the width direction;the load capacity of the curved laminate increases with the increase of its thickness;the distance between the onset location of the delamination and the inner surface of the curved laminate becomes greater with the curved laminate being thicker,but the ratio between this distance to the thickness of the curved laminate is smaller with the curved laminate being thicker;the onset location of the delaminate is closer to the loading end of the curved laminate with the curved laminate being thicker.

关 键 词：复合材料 弯角 应力分布 失效 厚度 

分 类 号：V214.8[航空宇航科学与技术—航空宇航推进理论与工程]