复合材料机身框轴向压缩屈曲分析与研究
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    摘要:

    通过试验研究了复合材料机身框承受轴向压缩载荷下的失效模式,并与工程理论计算、有限元分析进行对比。试验研究的框构型包含“C”型框和“Z”型框,试验结果显示,复合材料机身框与蒙皮结构在承受沿框方向的轴向压缩载荷时,首先蒙皮发生局部屈曲;随着载荷的增大,框腹板和内缘也发生局部屈曲,最终导致整个框截面的破坏。对蒙皮局部屈曲采用两加载边简支、两侧边固支的层压平板屈曲工程分析方法,分析结果表明,工程理论计算与试验数据吻合良好,并且理论值具有保守性。对于框腹板及框内缘这类薄壁结构,其边界支持作用弱于简支,导致工程理论计算结果不保守。为了获得框腹板与框内缘更准确的局部屈曲结果,必须采用几何非线性有限元建模分析。

    Abstract:

    The failure modes of the composite fuselage frame under axial compression are studied through experiments, and compared with the engineering theoretical calculation and finite element analysis. The frame configurations of experimental study includes “C” frame and “Z” frame. The test results show that when the composite fuselage frame and skin structure bear the axial compression load along the direction of frame, the skin occurs local buckling first. With the increase of the load, the web and inner edge of the frame also occur local buckling, which eventually leads to the failure of the entire frame section. For local buckling of skin,the buckling engineering method of laminated plates with two loading sides simplified-supported and the others clamped-supported is used to analyze the local buckling of skin. The analysis results show that the engineering theoretical calculation is in good agreement with the experimental data, and theoretical calculation values are conservative. For thin-walled structures such as frame webs and frame inner edges, the boundary support is weaker than the simple support, which results in unconservative engineering theoretical calculation. In order to obtain more accurate local buckling results of web and inner edge of frame, geometric nonlinear finite element modeling analysis is necessary.

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陆磊,许家宝,李洁玉.复合材料机身框轴向压缩屈曲分析与研究[J].民用飞机设计与研 究,2021(1):69-75LU Lei, XU Jiabao, LI Jieyu.[J]. Civil Aircraft Design and Research,2021,(1):69-75. ( in Chinese)

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  • 在线发布日期: 2021-04-07
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