针对某型飞机某部位复合材料加筋板蒙皮不同深度分层损伤,验证胶接挖补修理工艺效果。开展修理用胶粘剂的选型试验,设计了修理所需胶粘剂在不同试验温度环境下的拉伸剪切试验和90°剥离试验,通过研究胶粘剂的剪切强度和90°剥离强度随温度升高的变化规律,对比验证了J-200-2胶粘剂和J-272中温固化胶膜的性能参数。结果表明:J-272胶膜对高低温环境更敏感,性能差异较大,确定可采用J-200-2作为修理用胶粘剂;为验证采用J-200-2胶粘剂胶接挖补修理的效果,对典型加筋板蒙皮1/2和1/4处分层损伤进行修理,并进行轴压试验,对比修理试验前后数据,发现加筋板承载能力分别提高了20%和14.3%。选取典型加筋板蒙皮1/2处分层损伤,利用有限元分析软件验证修理效果,发现破坏载荷较未修理的409.8kN提升至501.1kN,经挖补修理后承载能力较未修理提高22%,具有较好的修理效果。
In view of the lamination damage of composite stiffened panel in a part of the aircraft,the effect of scarf repair was verified.By comparison of the tensile shear strength and peel strength at different temperatures to confirm the adhesive between J-200-2 and J-272.The results showed that J-272 film was more sensitive to temperature.In order to verify the repair effect of using J-200-2 adhesive,the damage of typical stiffened panel skin 1/2 and 1/4 layers were repaired.The results showed that the bearing capacity was increased by 20% and 14.3% respectively.Based on the software of ABAQUS,a finite element model was developed in the study simulating the axial compression strength and failure mode of repaired specimens.The failure load was increased 22% from 409kN to 501.1kN.The finite element analysis proved that the J-200-2 adhesive had satisfied repair effect.
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基金资助
芜湖市科技计划项目(2018pt01)
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