Analysis reveals effects of fastener configuration and material parameters on damping properties.
Due to the extensive application of composite materials in aircraft, the vibration problem of composite joint structures is particularly important for the safety and reliability of aircraft structure. In this article, in order to acquire the optimized damping properties, the dynamic properties of single lap composite joint structures are analyzed under varying structure and material, and the advanced embedded co‐cured damping composite is used as the basic material. The results obtained show that the thickness of the composite and viscoelastic layer can greatly improve the damping properties of composite joint structures within a certain range, and the shear modulus of the viscoelastic layer is 1.0 MPa with optimal damping properties. With the increase of the end distance ( e/d ), the damping properties are improved, and the effect of the edge distance ( w/d ) on the damping properties is limited. In addition, the damping properties of composite joint structures decrease with the increase of the structure length ( b ), and the frequency of composite joint structures increases with the increase of the stiffness of composite joint structures.
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Zhao et al. (2025) studied this question.
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