航空复合材料加筋板剪切稳定性及后屈曲承载性能  

Stability and post-buckling carrying capacity of aeronautic composite stiffened panel under shear loading

作　　者：谭翔飞[1] 何宇廷[1] 冯宇[1] 安涛[1] 张天宇 

机构地区：[1]空军工程大学航空航天工程学院,西安710038

出　　处：《复合材料学报》2018年第2期320-331,共12页Acta Materiae Compositae Sinica

基　　金：国家自然科学基金(51475470)

摘　　要：开展了复合材料加筋板剪切稳定性试验,研究了加筋板在承剪状态下的屈曲载荷、屈曲模态、后屈曲承载性能及破坏模式。试验结果表明,加筋板在剪切屈曲载荷下形成的屈曲波长轴线与加强件轴线夹角约45°,当屈曲比达到1.2时,存在二次屈曲行为,最终破坏载荷约为屈曲载荷的1.28倍;加筋板在二次屈曲失稳前,加强件几乎保持直线,起"屈曲分隔"的作用。结合试验现象,进行了加筋板剪切屈曲及后屈曲性能理论分析,得出的理论屈曲载荷与试验屈曲载荷的相对误差为7.2%,后屈曲阶段的理论载荷-应变曲线与试验结果的相对误差在10%以内,并确定了后屈曲角随屈曲比的变化规律。Shear stability experiments on aeronautic composite stiffened panel were conducted to investigate the buckling load,buckling mode,post-buckling carrying capacity and failure characterization.The results show the centric lines of buckling waves have an angle of 45°with the direction of stiffeners under shear buckling load.The re-buckling behaviors will occur when the buckling ratio reaches 1.2.Failure load is 1.28 times of the buckling load.The stiffeners work as‘skin buckling separated＇before re-buckling,and have little deformation.Theoretical analysis on the buckling and post-buckling behaviors was carried out.The buckling load by theoretical analysis is in agood agreement with experimental results with an error of 7.2%.Additionally,the slope of load-strain curve in post-buckling stage by theoretical analysis also leads an error less than 10% compared with experimental data.Finally,the variation law of the post-buckling angle and buckling ratio was determined.

关 键 词：复合材料加筋板 剪切 屈曲 后屈曲 理论分析 

分 类 号：V23[航空宇航科学与技术—航空宇航推进理论与工程] TB330.1[一般工业技术—材料科学与工程]