【摘要】 为研究不同修理方法以及不同损伤尺寸对复合材料层合板拉伸性能的影响,针对复合材料飞机蒙皮,设计了无损板、60 mm与30 mm损伤孔径的胶接修理板和胶铆混合修理板五组试验件,并对这五组结构件进行静强度拉伸试验及失效机理分析。建立试验件的三维有限元仿真模型,分析无损板和四组修理件的破坏强度、破坏模式、应力分布、应力大小和危险部位。结果证明,胶铆混合修理可以改变复合材料修理结构件的应力分布,并有效降低危险部位的应力集中,改善结构的强度恢复率。更多还原

【Abstract】 In order to study the influence of different repair methods and different damage sizes on the tensile properties of composite laminates,experimental investigation on static tensile strength was designed and carried out in this paper with five groups of test specimens,including no-damage specimens,adhesive repair specimens and adhesive-rivet hybrid repair specimens with 60 mm and 30 mm circular hole damage for composite aircraft skin.The three-dimensional finite element simulation models of the test specimens were established,to analyze the difference between the five groups of specimens in terms of failure strength,failure mode,stress values and distribution,and critical sites.The results show that the adhesive-rivet hybrid repair method is a better choice which changes the stress distribution of composite repaired parts,reduces the stress concentration effectively in the critical sites,and improves the strength recovery rate of the structure.更多还原