Compressive buckling and post-buckling behaviors of J-type composite stiffened panel before and after impact load

Wu, Qianqian; Hu, Shaojie; Tang, Xiao‐Han; Liu, Xin; Chen, Zongbing; Xiong, Jian

doi:10.1016/j.compstruct.2022.116339

Cited by 14 publications

(3 citation statements)

References 38 publications

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“…The study explores the complex interactions in large-scale structures, providing crucial insights for design considerations. Wu et al [9] investigate the compressive buckling and post-buckling behaviors of J-type composite stiffened panels before and after impact load. The paper addresses the dynamic aspects of post-buckling, considering the effects of impact, and provides insights into structural resilience.…”

Section: Introductionmentioning

confidence: 99%

Virtual Full Scale Static Test of a Civil Tilt Rotor Composite Wing in Non-Linear Regime

Chiariello,

Perillo,

Linari

et al. 2024

Aerospace

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This study addresses the crucial role of post-buckling behavior analysis in the structural design of composite aeronautical structures. Traditional engineering practices tend to result in oversized composite components, increasing structural weight. EASA AMC 20-29’s Building Block Approach suggests phased testing, but its time and cost challenges necessitate a shift to high-fidelity post-buckling analyses, exemplified by MSC NASTRAN SOL 400. This approach, showcased in the analysis of the Next Generation Civil Tilt Rotor Technology Demonstrator’s wing (NGTCTR-TD), effectively de-risks static tests, contributing to a more efficient certification process. The study demonstrates how advanced simulations provide detailed insights into local buckling phenomena, allowing precise stress distribution analysis. These analyses eliminate the risk of structural failure, paving the way for safer, more efficient, and cost-effective airframe structures. Future developments aim to validate numerical analyses with experimental data, further emphasizing the reliability and benefits of high-fidelity simulations.

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Section: Introductionmentioning

confidence: 99%

Virtual Full Scale Static Test of a Civil Tilt Rotor Composite Wing in Non-Linear Regime

Chiariello,

Perillo,

Linari

et al. 2024

Aerospace

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“…In addition to T-and cap-type structures, carbon fiber composite J-type structures provide a lightweight and efficient solution by distributing applied loads more efficiently, reducing stress concentrations, and improving overall structural integrity. J-type reinforced wall panels provide a lightweight and efficient solution by increasing strength and stiffness as well as improving load distribution along the structure [7]. Therefore, exploring its mechanical load carrying capacity and failure mechanism has become an important strategy for the design and optimization of Jtype structures.…”

Section: Introductionmentioning

confidence: 99%

Study on bearing capacity and damage mode of carbon fiber composite J-type structures in oilfield completion tool connections

Lu,

Sun,

Zou

et al. 2024

J. Phys.: Conf. Ser.

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Carbon fiber composite structures have a broad application prospect in oilfield completion tool module connection. However, the material failure mechanism is still unclear. In this paper, the mechanical properties and failure mode of T700/7901 composite J-type structure are investigated from experimental and finite element perspectives. Firstly, the load-carrying and failure properties of the structure were analyzed through typical mechanical property experiments such as tensile, bending, and compression, and the fiber, matrix damage, and delamination damage are the main reasons for the failure of the mechanical properties of the material. Secondly, a numerical model of the progressive damage ontological relationship of the composite material was established, and the accuracy of the model was verified by combining the experimental results. Based on the above study, this paper proposes the failure mechanism and optimization of composite J-type, which provides useful guidance for the design of fiber composite structures for oilfield completion tool types in the future.

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“…A [ 13 ] applied analysis of continuous damage mechanics and cohesive elements to establish intralaminar and interlaminar models, predicted the responses of large composite stiffened panels to low-speed impact and compression after impact, and discussed the effects of parameters including penalty stiffness and element size on the results of the numerical model. Wu Xiaoyang [ 14 ] and Wu Qianqian [ 15 ] investigated the buckling and post-buckling loads of composite stiffened panels under multi-point impact damage experimentally and by simulation. Within the existing research on impact and compression after impact in composite stiffened panels, most scholars have focused on the damage modes caused by impact, and the effects of impact damage on compression.…”

Section: Introductionmentioning

confidence: 99%

An Experimental and Numerical Study on Impact and Compression after Impact of Stiffened Composite Panels

et al. 2022

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To develop the full application potential of composite materials, research on the post-buckling behavior of composite stiffened panels is of great significance. In this paper, the impact and compression after impact (CAI) behaviors of four different types of composite stiffened panels were studied by numerical simulation and experimental methods. The low-velocity impact damage simulated dynamically was introduced as the initial state in the compression simulation, and a two-dimensional shell model with Hashin failure criteria and stiffness degradation was adopted to estimate the failure load of composite stiffened panels under impact and CAI. The error between simulation results and test results was less than 10%, showing that the method used in this study achieved considerable accuracy in experimental results. Analysis of the impact test results revealed that the extent of damage is related to many factors, including the cross-sectional size of stiffeners, the spacing of stiffeners, and the material and thickness of the skin. In addition, the influence of fatigue damage on residual strength after impact was also studied experimentally, with results showing that the buckling and failure loads decreased by about 5% under 106 flight fatigue loads. However, there were obvious fluctuations in the load-displacement curves, which may have been caused by debonding between the stiffeners and the skin. Experimental results and the simulation matrix show that the post-buckling ratio increased with the increase of the stiffness ratio, then was stable after 2.0. Furthermore, the thinner the skin, the greater the post-buckling ratio. The experimental and simulation results provide an important reference for the structural design and failure-mechanism analysis of composite stiffened panels.

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Compressive buckling and post-buckling behaviors of J-type composite stiffened panel before and after impact load

Cited by 14 publications

References 38 publications

Virtual Full Scale Static Test of a Civil Tilt Rotor Composite Wing in Non-Linear Regime

Virtual Full Scale Static Test of a Civil Tilt Rotor Composite Wing in Non-Linear Regime

Study on bearing capacity and damage mode of carbon fiber composite J-type structures in oilfield completion tool connections

An Experimental and Numerical Study on Impact and Compression after Impact of Stiffened Composite Panels

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