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On the flutter of matrix cracked laminated composite plates reinforced with graphene nanoplatelets
Abstract This paper investigates graphene nanoplatelets (GPLs) reinforced composite (GPLRC) with matrix cracks by using element-free IMLS-Ritz method. The effective Young's modulus of each GPLRC layer is determined by the modified Halpin-Tsai micromechanics model while its Poisson's ratio and mass density are predicted according to the rule of mixtures. The degraded stiffness of cracked layers is modeled via the self-consistent micromechanical model. The first-order shear deformation theory and first-order piston theory are employed to formulate aeroelastic model. Element-free IMLS-Ritz method is applied to discretize the equation of motion. The accuracy of the IMLS-Ritz results is examined by comparing the natural frequency and critical aerodynamic pressure with those obtained from published values. A comprehensive parametric study is carried out, with a particular focus on the effects of matrix crack density, distribution pattern, weight fraction, total number of layers, geometry of GPLs, and aspect ratio of plates on the flutter bound of matrix cracked GPLRC plates.
Highlights Flutter model of matrix cracked GPLRC plates under supersonic flow is developed using the first-order shear deformation theory and element-free IMLS-Ritz method. Degraded stiffness due to matrix cracks is introduced by using the self-consistent model. Accurate natural frequencies of matrix cracked GPLRC plates under different aerodynamic pressure are obtained and verified. Both mode exchange and mode merger (flutter) are revealed for different matrix crack parameter. Increasing GPLs weight fraction, length to thickness ratio of GPLs, or decreasing length to width ratio of GPLs, aspect ratio of GPLRC plate will enlarge flutter bound.
On the flutter of matrix cracked laminated composite plates reinforced with graphene nanoplatelets
Abstract This paper investigates graphene nanoplatelets (GPLs) reinforced composite (GPLRC) with matrix cracks by using element-free IMLS-Ritz method. The effective Young's modulus of each GPLRC layer is determined by the modified Halpin-Tsai micromechanics model while its Poisson's ratio and mass density are predicted according to the rule of mixtures. The degraded stiffness of cracked layers is modeled via the self-consistent micromechanical model. The first-order shear deformation theory and first-order piston theory are employed to formulate aeroelastic model. Element-free IMLS-Ritz method is applied to discretize the equation of motion. The accuracy of the IMLS-Ritz results is examined by comparing the natural frequency and critical aerodynamic pressure with those obtained from published values. A comprehensive parametric study is carried out, with a particular focus on the effects of matrix crack density, distribution pattern, weight fraction, total number of layers, geometry of GPLs, and aspect ratio of plates on the flutter bound of matrix cracked GPLRC plates.
Highlights Flutter model of matrix cracked GPLRC plates under supersonic flow is developed using the first-order shear deformation theory and element-free IMLS-Ritz method. Degraded stiffness due to matrix cracks is introduced by using the self-consistent model. Accurate natural frequencies of matrix cracked GPLRC plates under different aerodynamic pressure are obtained and verified. Both mode exchange and mode merger (flutter) are revealed for different matrix crack parameter. Increasing GPLs weight fraction, length to thickness ratio of GPLs, or decreasing length to width ratio of GPLs, aspect ratio of GPLRC plate will enlarge flutter bound.
On the flutter of matrix cracked laminated composite plates reinforced with graphene nanoplatelets
Guo, Hulun (author) / Yang, Tianzhi (author) / Żur, Krzysztof Kamil (author) / Reddy, J.N. (author)
Thin-Walled Structures ; 158
2020-09-15
Article (Journal)
Electronic Resource
English
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| British Library Online Contents | 2016
| British Library Online Contents | 2018