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Thermal Buckling Analysis of Stiffened Composite Cutout Panels
In aeroplanes, ships, and hypersonic space vehicles, stiffened plates with cutouts are often used. Aerodynamic heating produced by the interaction between the environment and the vehicle's surface quickly heats up this structural component. These activities affect the buckling characteristics of perforated plates and may result in an early failure due to the presence of cuts. This impact is avoided by properly stiffening the area surrounding the cutout. Thermal buckling effects must, thus, be taken into account when designing and analyzing thin-walled structural components. Using finite-element techniques, the effect of high temperatures on the buckling stresses of composite laminates with and without reinforced cuts is studied. This is accomplished via the use of a nine-noded heterosis element and a three-noded quadratic beam element. A transformation matrix ensures the displacement compatibility of the plate and stiffener. Thermal buckling of layered panels with cutouts is analyzed by employing eccentric stiffeners. It is witnessed from this investigation that various parameters significantly affect the buckling behavior of stiffened plates. These factors include cutout size, material anisotropy, thermal expansion ratio, modulus ratio, and boundary conditions.
Thermal Buckling Analysis of Stiffened Composite Cutout Panels
In aeroplanes, ships, and hypersonic space vehicles, stiffened plates with cutouts are often used. Aerodynamic heating produced by the interaction between the environment and the vehicle's surface quickly heats up this structural component. These activities affect the buckling characteristics of perforated plates and may result in an early failure due to the presence of cuts. This impact is avoided by properly stiffening the area surrounding the cutout. Thermal buckling effects must, thus, be taken into account when designing and analyzing thin-walled structural components. Using finite-element techniques, the effect of high temperatures on the buckling stresses of composite laminates with and without reinforced cuts is studied. This is accomplished via the use of a nine-noded heterosis element and a three-noded quadratic beam element. A transformation matrix ensures the displacement compatibility of the plate and stiffener. Thermal buckling of layered panels with cutouts is analyzed by employing eccentric stiffeners. It is witnessed from this investigation that various parameters significantly affect the buckling behavior of stiffened plates. These factors include cutout size, material anisotropy, thermal expansion ratio, modulus ratio, and boundary conditions.
Thermal Buckling Analysis of Stiffened Composite Cutout Panels
Lecture Notes in Civil Engineering
Ranadive, M. S. (editor) / Das, Bibhuti Bhusan (editor) / Mehta, Yusuf A. (editor) / Gupta, Rishi (editor) / Chandra, K. S. Subash (author) / Rajanna, T. (author) / Rao, K. Venkata (author)
2022-09-28
14 pages
Article/Chapter (Book)
Electronic Resource
English
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