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Buckling and post-buckling analysis of composite wing box under loads with torsion-bending coupling
https://orcid.org/0000-0001-8914-1210
Highlights A mathematical model for buckling and post-buckling under different torsion-bending ratios were established. The buckling stability and load carrying capacity of the wing box were analyzed by the experiments. By establishing a refined simulation model, the impact of different torsion-bending ratio on failure mode of the wing box.
Abstract In this paper, a mathematical model for the effect of different torsion-bending ratios on buckling and failure loads under complex operating conditions was proposed, and the buckling, post-buckling and failure behavior and mechanism of carbon fiber composite wing box were studied by combining experiments and simulations. A high-precision computational simulation model was established by considering detailed bolt arrangement information, as well as damage and failure of composite materials. The predicted buckling loads, failure loads, and damage modes are in good agreement with the experimental results. The results show that, under the condition of constant bending moment, as the torque increases, the linear strain of the box section remains consistent, while the shear strain increases significantly, leading to a change in the buckling mode and failure distribution. When the torsion-bending ratio is less than 2.0, the loading form of the structure is greatly affected by the torque. On the contrary, the buckling and failure loads are exponentially close to the pure torsional state. The mathematical model and simulation model in this study can provide an important reference for the structural design and failure mechanism analysis of large composite wing boxes.
Buckling and post-buckling analysis of composite wing box under loads with torsion-bending coupling
https://orcid.org/0000-0001-8914-1210
Highlights A mathematical model for buckling and post-buckling under different torsion-bending ratios were established. The buckling stability and load carrying capacity of the wing box were analyzed by the experiments. By establishing a refined simulation model, the impact of different torsion-bending ratio on failure mode of the wing box.
Abstract In this paper, a mathematical model for the effect of different torsion-bending ratios on buckling and failure loads under complex operating conditions was proposed, and the buckling, post-buckling and failure behavior and mechanism of carbon fiber composite wing box were studied by combining experiments and simulations. A high-precision computational simulation model was established by considering detailed bolt arrangement information, as well as damage and failure of composite materials. The predicted buckling loads, failure loads, and damage modes are in good agreement with the experimental results. The results show that, under the condition of constant bending moment, as the torque increases, the linear strain of the box section remains consistent, while the shear strain increases significantly, leading to a change in the buckling mode and failure distribution. When the torsion-bending ratio is less than 2.0, the loading form of the structure is greatly affected by the torque. On the contrary, the buckling and failure loads are exponentially close to the pure torsional state. The mathematical model and simulation model in this study can provide an important reference for the structural design and failure mechanism analysis of large composite wing boxes.
Buckling and post-buckling analysis of composite wing box under loads with torsion-bending coupling
https://orcid.org/0000-0001-8914-1210
Highlights A mathematical model for buckling and post-buckling under different torsion-bending ratios were established. The buckling stability and load carrying capacity of the wing box were analyzed by the experiments. By establishing a refined simulation model, the impact of different torsion-bending ratio on failure mode of the wing box.
Abstract In this paper, a mathematical model for the effect of different torsion-bending ratios on buckling and failure loads under complex operating conditions was proposed, and the buckling, post-buckling and failure behavior and mechanism of carbon fiber composite wing box were studied by combining experiments and simulations. A high-precision computational simulation model was established by considering detailed bolt arrangement information, as well as damage and failure of composite materials. The predicted buckling loads, failure loads, and damage modes are in good agreement with the experimental results. The results show that, under the condition of constant bending moment, as the torque increases, the linear strain of the box section remains consistent, while the shear strain increases significantly, leading to a change in the buckling mode and failure distribution. When the torsion-bending ratio is less than 2.0, the loading form of the structure is greatly affected by the torque. On the contrary, the buckling and failure loads are exponentially close to the pure torsional state. The mathematical model and simulation model in this study can provide an important reference for the structural design and failure mechanism analysis of large composite wing boxes.
Buckling and post-buckling analysis of composite wing box under loads with torsion-bending coupling
Wang, Peiyan (author) / Chen, Yongshun (author) / Pei, Runa (author) / Lian, Chenchen (author) / Zhang, Ke (author) / Zhou, Yinhua (author)
Thin-Walled Structures ; 193
2023-10-09
Article (Journal)
Electronic Resource
English
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