先进复合材料薄壁加筋板轴压屈曲特性及后屈曲承载性能  

Buckling and Post-buckling Performance of Advanced Composite Stiffened Panel Under Compression

作　　者：张浩宇[1] 何宇廷[1] 冯宇[1] 谭翔飞[1] 郑洁[2] 

机构地区：[1]空军工程大学航空航天工程学院,西安710038 [2]中航工业第一飞机设计研究院,西安710089

出　　处：《航空材料学报》2016年第4期55-63,共9页Journal of Aeronautical Materials

基　　金：国家自然科学基金(51475470)

摘　　要：对国产先进复合材料薄壁加筋板结构进行了轴向压缩试验。通过监测典型位置的应变和离面位移,研究了该型加筋板的轴压屈曲及后屈曲性能。应用工程算法对试验件的蒙皮初始屈曲载荷和屈曲模态进行了预测,试验结果表明,该型加筋板的轴压屈曲形式依次是筋条间蒙皮的初始屈曲、部分蒙皮的二次屈曲以及4根筋条的柱屈曲;蒙皮发生屈曲后,蒙皮承担的部分载荷转移至筋条,使筋条成为主要承力部分,当筋条发生断裂后,试验件迅速整体破坏;其破坏载荷平均值为482.67 k N,屈曲载荷的平均值为204 k N,前者为后者的2.37倍,说明该型结构具有很大的后屈曲承载空间。The axial compressive experiment was conducted on the domestic advanced composite stiffened panel,and its buckling and post-buckling performance was analyzed by monitoring strain and out-of-plane displacement of typical positions. The initial buckling load and buckling mode of panels were calculated by engineering methods to direct the follow-up axial compressive experiment. The experimental results show that the buckling patterns are mainly local buckling of panels between stiffeners,the second buckling of few positions of panels and cylindrical buckling of all 4 stiffeners successively; after local buckling of panels,part of load bearded by panels before is transferred to stiffeners and then stiffeners become the main bearing part; after fracture failure of stiffeners,the specimen is destroyed rapidly; the average value of failure load is 482. 67 k N,which is 2. 37 times of 204 k N of the average value of buckling load;the composite stiffened panel can bear more load after buckling.

关 键 词：复合材料 加筋壁板 屈曲载荷 屈曲模态 后屈曲 

分 类 号：TB332[一般工业技术—材料科学与工程]