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针对平纹编织复合材料在航空中的不断应用与该类型层板维修研究的缺失性,根据不同附加铺层的平纹编织复合材料层板维修工况,进行了三维有限元模型分析计算,制订了综合母板、胶层、补片的多重失效准则,并进行了相应的试验验证,得到结论如下:附加层的铺设对于提高修补板强度有积极的效果,试验中发现增加附加铺层数会由于粘接区域的增加,而导致更多的维修缺陷影响恢复效果,建议修理中附加铺层数不宜过多;铺层条件下的平纹编织碳纤维/环氧材料层板结构最佳附加铺层为一层,结构最高修复强度恢复率达到了65.57%,该结论也可为其他类型的平纹编织复合材料层板维修提供参考。分析过程中采用的三维有限元修补模型得到的强度值和破坏区域与试验数据基本吻合,说明计算模型与失效准则能够满足维修设计的需求,为实际修理提供较为准确的参考指标。
Aiming at the continuous application of plain weave composites in aviation and the lack of research on this type of laminates maintenance, the three-dimensional finite element model is analyzed and calculated according to the maintenance condition of plain weaved laminates with different additional layers, Multi-layer failure criteria of masters, glue layers and patches, and the corresponding tests were conducted. The conclusions are as follows: The laying of additional layers has a positive effect on improving the strength of patch panels. Then increase the area, which led to more maintenance defects affect the recovery effect, it is recommended that the number of additional repair shop should not be too much; lay flat woven carbon fiber / epoxy laminate best additional layer structure as a layer , The highest recovery rate of the structure reached 65.57%. This conclusion can also provide reference for the maintenance of other types of plain weave composite laminates. The strength values and failure zones obtained by the three-dimensional finite element model used in the analysis are in good agreement with the experimental data, indicating that the calculation model and failure criterion can meet the requirements of maintenance design and provide a more accurate reference index for actual repair.