Assessment of numerical modeling approaches for thin composite laminates under low-velocity impact

Huang, Linhai; Yin, Tao; Sun, Jie; Zhang, Diantang; Zhao, Junhua

doi:10.1016/j.tws.2023.111053

Cited by 6 publications

(1 citation statement)

References 23 publications

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“…Also various stiffening methods such as application of fiber-metal laminates [20,21], 3D woven [22,23] and angle-interlock woven fibers [8] have been proposed to increase the out-of-plane strength of the laminates. Huang et al [24] demonstrated the main influence of the damage evolution algorithm for assessment of the impact response in the composite laminates. Broekel and Prusty [25] demonstrated a small advantage for application of stiffeners to increase strength of the laminates under uniform transverse loads.…”

Section: Introductionmentioning

confidence: 99%

Influence of residual strength on progressive collapse of GFRP composite panels under transverse loading

Nazari,

Taheri,

Khanzadeh-Moradllo

2024

Preprint

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Collapse of panels under transverse loads has been reported dependent on formation of some unstable subregions surrounded by failure lines (hinges) within the panels, however such a collapse mechanism has been less investigated for the composite panels. In this paper, the significance of residual strength in the flexural failure lines around the unstable subregions through the collapse of GFRP panels was investigated. In the experimental program, the panels made of E-glass/vinylester composite laminates with various layups and aspect ratios were examined. To observe progression of failure lines in the panels due to large deflections, by application of a support composed of tubular components, the restraining influence of support on the panels was minimized. Based on well-known criteria, initiation and evolution of damage in the composite panels were simulated using the FE models. By a good estimation from the compressive residual strength in the failure lines based on the results of uniaxial compressive and three-point-bending tests, the FE models could simulate softening of the composite panels prior to collapse and temporary stability prior to complete loss of load carrying capacity. Using the FE models, contribution of various strain components in the flexural failure of the laminates and the influence of residual strength on the energy absorption capacity was probed for various configurations of the laminates.

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