Experimental and numerical analyses of stiffened composite panels with delamination under a compressive load

Bai, Yujiao; Xu, Zhonghai; Song, Jieren; Miao, Linlin; Cai, Chaocan; Fan, Yang; Wang, Rongguo; He, Xiaodong; Hong, Yang; Dong, Xulun

doi:10.1177/0021998319875209

Cited by 10 publications

(4 citation statements)

References 36 publications

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“…Hence, CFRP structure has been increasingly applied to industries such as airspace. [1][2][3] T-joints are commonly adopted in the design of CFRP structure (Figure 1A), in which the perpendicular part of the stiffener (rib web) divides into two flanges that connect to the skin. Minimum radius is required to maintain the continuity and effective load transmission where the rib web curves into flanges, 4,5 leaving a deltoid cavity at the junction (Figure 1B) that is often filled with CFRP prepreg.…”

Section: Introductionmentioning

confidence: 99%

“…Carbon fiber reinforced composites (CFRP) has the capacity of bearing equal force strength with lighter weight compared to metal materials. Hence, CFRP structure has been increasingly applied to industries such as airspace 1–3 . T‐joints are commonly adopted in the design of CFRP structure (Figure 1A), in which the perpendicular part of the stiffener (rib web) divides into two flanges that connect to the skin.…”

Section: Introductionmentioning

confidence: 99%

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Aminated carbon nanotube enhanced composite T‐joints mediating CFRP load‐bearing capacity improvement

Bai,

Yan,

et al. 2023

Polymer Composites

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Adhesive bond is the weakest part of carbon fiber reinforced composites (CFRP) force‐bearing structure. Therefore, enhancing the strength of the adhesive bond is key to improve force‐bearing structure. In this study, adhesive strength of the common CFRP T‐joint was enhanced by aminated carbon nanotubes (CNT). To begin with, shear tensile strength of single‐lap‐joint laminated composites with various CNT content was verified, which peaked at 0.5 wt%. It was indicated that the adhesive bond of deltoid is the weakest area in a T‐joint. CNT was applied in the deltoid of composite T‐joint and pull‐off test was conducted to investigate the progress from the initiation and evolution of damage as well as the final failure. The aminated CNT employed in this study formed an effective load transmission through physical engagement and chemical bonding; the addition of 0.5 wt% CNT effectively enhanced tensile strength and toughness, improving mechanical property of the adhesive bond. This study provides a solution to enhance the adhesive area of CFRP load‐bearing structure with CNT, consequently improve the load‐bearing strength of composite.Highlights Aminated CNT is substantially improve the adhesive strength of CFRP T‐joint. Tensile strength and toughness of T‐joint deltoid was optimized by 0.5 wt% CNT. Effective load transmission through physical engagement and chemical bonding.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Aminated carbon nanotube enhanced composite T‐joints mediating CFRP load‐bearing capacity improvement

Bai,

Yan,

et al. 2023

Polymer Composites

Self Cite

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“…Delamination of the reinforced rib plays a significant role in the strength of the stiffened panel, and subsequent fiber fracture leads to the ultimate failure of the composite stiffened panel. By studying the failure modes of the composite stiffened panels under tensile loads [ 15 ], compressive loads [ 16 , 17 , 18 ], shear loads [ 19 , 20 , 21 ], and with preexisting delamination defects [ 22 , 23 , 24 ], it is possible to use these failure modes to guide process improvements. Furthermore, investigating the effects of different process steps [ 13 ], process parameters [ 25 , 26 ], and fabric ply angles [ 27 , 28 ] on the performance of the composite stiffened panels can provide insights for improving process methods, enhancing molding quality, and optimizing structural design.…”

Section: Introductionmentioning

confidence: 99%

Preparation and Validation of a Longitudinally and Transversely Stiffened Panel Based on Hybrid RTM Composite Materials

Li¹,

Ma²,

Shen³

et al. 2023

Materials

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In the face of the difficulty in achieving high-quality integrated molding of longitudinally and transversely stiffened panels for helicopters by resin-matrix composite materials, we combine the prepreg process and the resin transfer molding (RTM) process to propose a hybrid resin transfer molding (HRTM) for composite stiffened panel structures. The HRTM process uses a mixture of prepreg and dry fabric to lay up a hybrid fiber preform, and involves injecting liquid resin technology. Using this process, a longitudinally and transversely stiffened panel structure is prepared, and the failure modes under compressive load are explored. The results show that at the injection temperature of the RTM resin, the prepreg resin dissolves slightly and has little effect on the viscosity of the RTM resin. Both resins have good miscibility at the curing temperature, which allows for the overall curing of the resin. A removable box core mold for the HRTM molding is designed, which makes it convenient for the mold to be removed after molding and is suitable for the overall molding of the composite stiffened panel. Ultrasonic C-scan results show that the internal quality of the composite laminates prepared using the HRTM process is good. A compression test proves that the composite stiffened panel undergoes sequential buckling deformation in different areas under compressive load, followed by localized debonding and delamination of the skin, and finally failure due to the fracture of the longitudinal reinforcement ribs on both sides. The compressive performance of the test specimen is in good agreement with the finite element simulation results. The verification results show that the HRTM process can achieve high-quality integrated molding of the composite longitudinally and transversely stiffened panel structure.

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“…In the study of stiffened panels with defects, Ji and Zhao et al 13 studied the debonding behavior with defects, adopted a progressive damage model to predict the expansion of interlaminar damage, and used a bilinear cohesion model to evaluate the debonding damage between skin and stiffener web, and the damage evolution law of this model was in good agreement with the experimental situation. In terms of damage location, Bai et al 14 explored the influence of different damage locations on the bearing capacity and failure mode of the stiffened panels by comparative analysis of the bearing capacity and failure mode of the ribs, skin, and interface bonding layer with elliptical damage under a compression load, as well as the verification of the finite element model. Jasto and Reinoso et al 15 conducted experimental analysis on the initial position and propagation path of T-stiffened panels damage and concluded that the damage started from the triangular position of the T-joint and expanded asymmetrically to both sides, which was consistent with the conclusion drawn by Zhu 16 and Cheng et al 17 .…”

Section: Introductionmentioning

confidence: 99%

Investigation of the out-of-plane load-bearing capacity of T1100/5405 composite T-stiffened panels

Huang

Zhang

Dong

et al. 2021

Sci Rep

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With the continuous improvement of the mechanical properties of composite materials, the adhesive interface performance of composite T-stiffened panels has become a critical factor in determining the overall structural strength. However, little work has been reported on the mechanical properties of adhesive interfaces in composite T-stiffened panels under lateral bending and shear loading. Especially, there is no clear explanation on the damage evolution law of structural properties for the interface with defects, which greatly influenced the use of T-stiffened composite structures. In this paper, the mechanical properties of T1100/5405 composite T-stiffened laminates under lateral bending and shear loading are experimentally and numerically investigated. The load-bearing capacities for the panels with intact and defected adhesive interfaces are compared, the damage evolution law of typical T-stiffened structures is further explored. Based on the continuum damage model (CDM) and the cohesive zone model (CZM), the constitutive models of the adhesive layer and the composite material are established respectively. Good agreements between experimental and numerical profiles illustrate that damages mainly occur on the loading side and the corner of the L-type ribs under lateral bending conditions, while damages extend from both sides of the interface layer to the center under shear loading. When a prefabricated defect exists, damages extend from the defect location along the loading direction. At the same time, the analysis shows that the lay-up of the surface layer, the chamfer radius, and the width of T-type ribs have a great influence on the structural load-bearing capacity, but less on the damage evolution form.

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Experimental and numerical analyses of stiffened composite panels with delamination under a compressive load

Cited by 10 publications

References 36 publications

Aminated carbon nanotube enhanced composite T‐joints mediating CFRP load‐bearing capacity improvement

Aminated carbon nanotube enhanced composite T‐joints mediating CFRP load‐bearing capacity improvement

Preparation and Validation of a Longitudinally and Transversely Stiffened Panel Based on Hybrid RTM Composite Materials

Investigation of the out-of-plane load-bearing capacity of T1100/5405 composite T-stiffened panels

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