轴压载荷下复合材料薄壁加筋板后屈曲承载能力分析与试验验证  

Post-buckling Study and Test Verification of Thin-walled Composite Stiffened Panel under Compression Load

作　　者：苏雁飞[1] 赵占文[1] 薛应举[1] 

机构地区：[1]中航工业第一飞机设计研究院,陕西西安710089

出　　处：《航空科学技术》2014年第12期26-29,共4页Aeronautical Science & Technology

摘　　要：为了研究复合材料薄壁加筋板结构的后屈曲承载能力以及影响后屈曲的主要因素,应用Abaqus软件对三种构型下的薄壁加筋板进行了有限元分析,并与试验结果进行对比。结果表明,复合材料薄壁加筋板结构在轴向压缩载荷下具有较大的后屈曲承载能力,有限元分析与试验得出的试验件后屈曲载荷均为初始屈曲载荷的7倍左右,蒙皮的厚度及筋条间距对加筋板的后屈曲承载能力影响不大,加筋板的后屈曲承载能力主要取决于筋条的刚度。在飞机结构设计中,可以充分利用薄壁加筋板结构的后屈曲承载能力来提高结构使用效率。The simulation and experiment of three different composite thin-walled stiffened panels from an aircraft fuselage were carried out in order to study their post-buckling response. It was found that the thin-walled composite stiffened panel has great post-buckling ability. The ratio of post-buckling load and initial buckling load was around 7 from both the ifnite element simulation and the experimental results. The post-buckling capability of the thin-walled composite stiffened panel was mainly determined by the stiffness of the stringer, but had little relationship with skin thickness and stringer pitch, and it can be applied in the aircraft design to increase the efifciency of structure.

关 键 词：复合材料 薄壁加筋板 轴压 后屈曲 

分 类 号：V216.1[航空宇航科学与技术—航空宇航推进理论与工程]