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Experimental and numerical investigation on the strength and load distribution of composite hybrid bonded-bolted joints
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DOI：10.1016/j.ijadhadh.2026.104354.png)
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Abstract
En 中文
Composite joints are critical to aircraft structural integrity, and hybrid bonded-bolted joints have emerged as a promising joining strategy. However, their load transfer mechanisms and failure behavior remain not fully understood. In this study, the strength performance of purely bolted joints, sealant-based hybrid joints, and structural-adhesive-based hybrid joints is systematically investigated through combined experiments and finite element simulations. A three-dimensional finite element model of a double-lap, two-fastener joint is developed, incorporating a user-defined material subroutine with the Hashin failure criterion to capture progressive damage in composite laminates. The results reveal that the use of high-stiffness structural adhesives may unexpectedly reduce the joint strength compared to purely bolted configurations. This counterintuitive behavior is attributed to debonding-induced non-uniform load redistribution, leading to asynchronous fastener loading and amplified stress concentration relative to purely bolted joints. Numerical investigations of the damage evolution further indicate that the ductility of the adhesive layer is a key parameter governing the synergistic load-sharing and cumulative strengthening effect between the adhesive and fasteners. This work provides new mechanistic insights into hybrid joint behavior and offers practical guidance for the design and optimization of composite bonded-bolted structures.
Keywords:
Composites
Hybrid bonded-bolted joints
Finite element analysis
Load distribution
Failure mode
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3.8K
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