Abstract Interference-fit is getting increasing attentions in the aerospace field owing to its excellent enhancement on the sealing and fatigue life of composites assembly, but the severe damage around the hole caused by installation is still a huge challenge. In this paper, a three-dimensional anisotropic non-linear progressive damage model based on continuum damage mechanics was developed to reveal the damage mechanism of carbon fiber reinforced plastic (CFRP) composites interference bolting with sleeve. The proposed model adopted strain-based failure criteria and non-linear damage evolution law to predict damage initiation and propagation of composite laminates. A cohesive model taking into account the traction-separation constitutive response was employed to capture the delamination behavior between the composite plies. The elastoplastic model was utilized to characterize the sleeve's deformation behavior. Numerical simulations of different installation modes are performed and compared with experiments. The inserting load, damage modes and damage positions predicted by the proposed model agree well with the experimental results. Moreover, it is also verified that the interference installation of sleeved fasteners can remarkably reduce the intra-laminar damage and avoid the inter-laminar delamination of composite laminates compared to the conventional bolt.

中文翻译：

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碳纤维增强塑料复合材料带套筒过盈螺栓损伤行为建模

摘要 过盈配合以其对复合材料装配体密封性和疲劳寿命的显着提高而在航空航天领域受到越来越多的关注，但安装造成的孔周围严重损坏仍然是一个巨大的挑战。本文建立了基于连续损伤力学的三维各向异性非线性渐进损伤模型，揭示了碳纤维增强塑料（CFRP）复合材料与套筒干涉螺栓连接的损伤机理。所提出的模型采用基于应变的失效准则和非线性损伤演化规律来预测复合材料层压板的损伤起始和扩展。考虑到牵引分离本构响应的内聚模型被用来捕捉复合层之间的分层行为。弹塑性模型用于表征套筒的变形行为。进行了不同安装方式的数值模拟，并与实验进行了比较。模型预测的插入载荷、损伤模式和损伤位置与实验结果吻合较好。此外，还验证了与传统螺栓相比，套筒紧固件的干涉安装可以显着减少层内损坏并避免复合层压板的层间分层。