Experimental investigation on low-velocity impact response of carbon/glass hybrid S-shaped foldcore sandwich structure

Deng, Yaxin; Li, Xiang; Hu, Xiaoyu; Wu, Huapeng; Zhou, Chunping; Lu, Peixiang

doi:10.1016/j.tws.2022.109921

Cited by 10 publications

(2 citation statements)

References 29 publications

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“…[4][5][6] Therefore, considering the aforementioned factors, numerous scholars have conducted pertinent research. [7][8][9][10] In light of the damage characteristics and mechanism of composite laminates under LVI, scholars have conducted experimental research based on various aspects such as laminate properties, 11 shape of impactors, 12 and impact angles. 13 Luv Verma et al 14,15 used pseudo elastic shape memory alloy as a reinforced body embedded in glass-fiber reinforced polymer composites to study its high-velocity (70, 85, 95, and 105 m/s) impact behavior and CAI properties.…”

Section: Introductionmentioning

confidence: 99%

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Effect of ultraviolet radiation on the low‐velocity impact and compression after impact performances of aerospace composite laminates

Liu,

Li,

Feng

et al. 2023

Polymer Composites

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The low‐velocity impact (LVI) characteristics and compression after impact (CAI) properties of aircraft composite laminates under the influence of ultraviolet (UV) radiation were studied. Firstly, 0, 30, 60, 90 days of UV radiation experiments were carried out on the specimens to analyze the characteristics of the surface topography. Secondly, LVI experiments, the impact energies of 10, 17, and 25 J, were carried out on specimens to analyze the impact response laws and the characteristics of the impact instantaneous deformation. Finally, through CAI experiments and scanning electron microscope (SEM) techniques to clarify the influence mechanism of UV radiation on the residual compressive strength of specimens. The results showed that with the increase of UV radiation time, the shrinkage and erosion phenomena of the surface matrix and the exposure degree of the surface fibers were gradually increased, and the surface fibers were completely exposed after 90 days of radiation. At the same impact energy, with longer radiation time, the peak force gradually decreased (from 8673.86 to 7851.68 N at 17 J), the absorbed impact energy (from 9.48 to 11.13 J at 17 J) and maximum displacement (from 4.1 to 4.73 mm at 17 J) increased, the depth of pit on the impact surface decreased (from 0.213 to 0.14 mm at 17 J), and the internal damage projection area increased (from 906.68 to 1158.66 mm2 at 17 J). The compression damage of the specimens not exposed to/ exposed to UV radiation was mainly fiber cracking/interlayer delamination, respectively.Highlights Ultraviolet (UV) radiation makes the matrix of surface shrink, the fibers exposure increase. The Stage II has obvious oscillation phenomenon in four stages of the low‐velocity impact process. With prolonged UV radiation, the projected area of internal damage expands. The residual compressive load increases with the increase of UV radiation time.

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Section: Introductionmentioning

confidence: 99%

“…All of these factors have the potential to cause damage or degradation to aircraft composite structures, thereby posing a threat to flight safety 4–6 . Therefore, considering the aforementioned factors, numerous scholars have conducted pertinent research 7–10 …”

Section: Introductionmentioning

confidence: 99%