【摘要】 作为机身壁板的主要机械连接方式，复合材料螺接部位的承载能力直接影响飞机的服役性能。本文设计制造了对称、非对称以及对称含垫片三种复合材料单钉搭接试样，通过试验研究获得各种单钉搭接试样的载荷—位移曲线和破坏模式。试验结果显示，搭接方式会显著影响单钉搭接结构的承载特征，非对称单钉搭接结构的承载性能主要由薄层决定，垫片会降低结构刚度，但是对承载能力的影响不大。建立单钉搭接结构力学性能数值仿真分析模型，对于单钉搭接试样最大载荷的预测误差在5%以内。结合试验与仿真结果，讨论了单钉搭接结构的失效机理，损伤以纤维压缩损伤和基体压缩损伤为主。本文研究结果可为航空复合材料搭接结构的优化设计提供参考。更多还原

【Abstract】 As a primary mechanical joining configuration for fuselage panels, the load-bearing capacity of composite material bolted joints directly influences the in-service performance of aircraft. Three kind of composite single bolt joint specimens-symmetric, asymmetric, and symmetric with shims-were designed and manufactured. Experimental investigations were conducted to obtain the load-displacement curves. The results indicate that the single lap joint configuration significantly influences the load-bearing characteristics. The load-bearing performance of asymmetric joints is primarily governed by the thin layer, while the shims reduce the linear structural stiffness, but have minimal impact on ultimate load capacity. A finite element simulation model for analyzing the mechanical properties of single-bolt lap joints was developed, achieving a prediction error within 5%. The failure mechanisms of the joints were discussed, revealing that damage is dominated by fiber compressive failure and matrix compression. The findings of this study provide valuable insights for optimizing the design of aerospace composite lap joint structures.更多还原