飞机复合材料蒙皮破孔胶接贴补修理力学模型及应用

doi:10.19936/j.cnki.2096-8000.20260628.015

摘要/Abstract

摘要： 为快速实现飞机复合材料破孔损伤贴补修理方案设计,建立了复合材料搭接接头承受复杂载荷的通用力学解析模型,并求解了蒙皮破孔贴补修理模型中轴向拉力导致的附加弯矩和剪力,进而得到接头重叠段的剪应力和剥离应力分布曲线。该结果与有限元分析结果较为接近,模型为贴补修理方案的快速设计和接头分析提供了有力支撑。模型结果表明,采用与原结构相同的板件制作贴补片,或适当增加搭接长度、胶层厚度,能获得更好的修复强度。

关键词: 复合材料, 贴补修理, 胶结接头, 力学解析, 有限元

Abstract: In order to quickly design repair plans for aircraft composite material perforation damage, a general mechanical analysis model for composite material lap joints under complex loads was established. The additional bending moment and shear force caused by axial tension in the skin perforation repair model were solved, and the distribution curves of shear stress and peel stress in the joint overlap section were obtained, which are close to the results of finite element analysis. This model provides strong support for the rapid design and joint analysis of maintenance plans. The model results indicate that using the same panel as the original structure for patching or appropriately increasing the overlap length and adhesive layer thickness can achieve better repair strength.

Key words: composite materials, patch repair, adhesive-bonded joint, mechanical analysis, finite elements

中图分类号:

TB332

梁赟, 王恒, 杨超军. 飞机复合材料蒙皮破孔胶接贴补修理力学模型及应用[J]. 复合材料科学与工程, 2026, 0(6): 137-145.

LIANG Yun, WANG Heng, YANG Chaojun. Mechanical model and application of adhesive repair for broken holes in aircraft composite skin[J]. COMPOSITES SCIENCE AND ENGINEERING, 2026, 0(6): 137-145.

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