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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。
In the process of manufacturing, the flaps of the aircraft composite flap flaps have some defects such as uneven thickness distribution and warpage. With ABAQUS finite element software, the article studies the strain distribution Impact. The results show that under the condition of axial compression, the thickness of the top and bottom of the curved plate is 15% and the strain error is up to 7%. The thickness of the curved plate is about 25% and the strain error is about 0.03% %; Curved warp inward 10mm, strain error of 3.3%. For aircraft manufacturing process of ultra-poor processing reference.