航空碳纤维树脂基复合材料加筋板压缩屈曲及后屈曲性能  

Buckling and post-buckling performance of aeronautic carbon fiber reinforced resin composite stiffened panel under compression

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

机构地区：[1]空军工程大学航空航天工程学院,西安710038

出　　处：《航空动力学报》2016年第10期2359-2369,共11页Journal of Aerospace Power

摘　　要：开展了复合材料加筋板轴压稳定性实验,对加筋板的屈曲及后屈曲性能、破坏模式和后屈曲失效表征进行了研究.实验结果表明加筋板在轴压下具有良好后屈曲承载潜能,破坏载荷约为屈曲载荷的2.2倍;其屈曲模式为筋条间蒙皮首先发生屈曲失稳,筋条在整个承载过程中保持直线,起到"屈曲分隔"的作用.通过对加筋板屈曲及后屈曲性能的理论分析,得出的理论屈曲载荷和理论破坏载荷与实验结果相对误差均小于8%,并确定了在后屈曲过程中蒙皮中心挠度的变化规律和轴向载荷的面内分布特征.Compressive experiments on aero composite stiffened panel were conducted to study the carrying capacity,failure modes and post-buckling failure characterization.The results showed that the composite stiffened panel had a high post-buckling carrying capacity.The failure load was almost 2.2times of the buckling load.The skin bay initiated buckling first.However,the stiffeners had no buckling before failure,which worked as‘skin buckling separated＇.According to the theoretical analysis,theoretical buckling and failure load had an error less than 8% compared with the experimental results.Additionally,the variation of the out-of-plane displacement on skin center and distribution of the axial compressive load were determined in the post-buckling process.

关 键 词：复合材料加筋板 屈曲 后屈曲 破坏模式 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] TB332[一般工业技术—材料科学与工程]