飞机复合材料襟翼前缘蒙皮曲板稳定性试验件在制造过程中存在厚度分布不均匀、翘曲等缺陷,借助ABAQUS有限元软件,文章研究前述缺陷对复合材料曲板受载时应变分布的影响.文章研究表明,轴压情况下,曲板上下厚度相差15%,应变误差达到7%;曲板左右厚度相差25%,应变误差为0.03%;曲板局部厚度偏厚0.065%,应变误差为1.8%;曲板向内翘曲10mm,应变误差为3.3%.供飞机制造过程中超差处理参考.%Some manufacturing defects such as uneven thickness distribution and warp often occur in the manufacturing process of curved plate buckling specimens of composite flap leading edge skins. The impact of these defects to the strain distribution of composite curved plate is studied in this article using the FEM software ABAQUS. This paper following results are obtained:strain error reaches 7%if the difference of upper and lower thicknesses of the curved plate is 15%;strain error is only 0.03%if the difference of left and right thicknesses of the curved plate is 25%;strain error is 1.8%if the local thickness is 0.065%thicker than other area of the curved plate;strain error is 3.3%if the inward warp of the curved plate is 10mm. These results provide useful references for the oversize treatment in aircraft manufacturing process.
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