Buckling and Vibration of Stiffened Panels or Single Plates with Clamped Ends

Watson, Andrew; Kennedy, David; Williams, F.W.; Featherston, Carol Ann

doi:10.1260/136943303769013228

Cited by 5 publications

(5 citation statements)

References 17 publications

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“…The plate was clamped along its loaded edges by restricting out-of-plane displacement and rotation. In order to speed up the process due to the large number of analyses required, this was achieved using a small number of point supports and a small number of wavelengths to represent the mode [32]. The remaining edges were simply supported by restricting out-of-plane displacement.…”

Section: Discussionmentioning

confidence: 99%

Buckling of optimised flat composite plates under shear and in-plane bending

Featherston

Watson

2005

Composites Science and Technology

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Section: Discussionmentioning

confidence: 99%

Buckling of optimised flat composite plates under shear and in-plane bending

Featherston

Watson

2005

Composites Science and Technology

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“…The plate was clamped along its loaded edges by restricting out-of-plane displacement and rotation. In order to speed up the process due to the large number of analyses required, this was achieved using a small number of point supports and a small number of wavelengths to represent the mode (Watson et al [9]). The remaining edges were simply supported by restricting out-of-plane displacement.…”

Section: Vicon Analysismentioning

confidence: 99%

“…In order to speed up the process due to the large number of analyses required, a small number of point supports were used to represent the line support and a small number of wavelengths were used to represent the mode (Watson et al [9]). The remaining edges were simply supported by restricting out-of-plane displacement.…”

Section: Figurementioning

confidence: 99%

Multilevel optimization of composite panels under complex load and boundary conditions

Featherston

Watson

2007

Struct Multidisc Optim

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This is by no means a trivial task. While the widely used finite element analysis (FEA) is very versatile, allowing structures with a wide range of loading and boundary conditions to 3 be analyzed, it comes at a high computational cost. This is particularly the case when performing design optimization involving large numbers of design variables, which requires many finite element analyses to be carried out.The specialist analysis and optimum design software VICON 2 is based on an 'exact' strip method, and so allows prismatic aerospace structural components, such as aircraft wing panels, to be analyzed in a much faster and more efficient way. However, while the software can analyze and design integral structural components whose cross-sections and loading are longitudinally invariant, it is unable to design a general 3-dimensional structure subject to a complex external loading. Typically, finite element analyses of the overall structural system are required to determine the loads acting on the individual structural components prior to any VICON analysis and optimization. Despite this and some approximations required by the modeling process, VICON has been used for analysis and design purposes, in both industry and academia, for more than a decade. Three different geometries of plate and nine panels with different aspect ratios and radii of curvature were examined. Each plate/panel was constructed from eight plies of carbon fibre epoxy pre-preg arranged in a balanced, symmetrical lay-up. In each case the lay-up was designed to optimise the buckling strength using a combination of VICON and the commercially available finite element analysis (FEA) code ABAQUS/Standard. Optimisation MethodIn order to determine the optimum design for each of the plates and panels, a two-stage process was undertaken.In the first stage, the software VICON was used to perform series of parametric studies on a model with simplified geometry, load and boundary conditions. In each of these studies the effect of varying ply orientation on the buckling load was investigated by altering the lay-up of each ply in five degree steps, whilst maintaining a balanced symmetric lay-up. Due to the efficiency of the analysis, it was possible to a large number of studies relatively quickly, thereby generating response surfaces plotting buckling load against lay-up for each geometry, from which an optimum design to this simplified problem could be selected.Following this initial optimisation, the finite element analysis software ABAQUS/Standard was used in combination with a more accurate model in terms of geometry load and boundary 5 conditions to perform a second study using a linear eigenvalue analysis based around the optima determined in the first stage using VICON.In this way each piece of software was used to its best effect, with the majority of analyses being carried out using the extremely efficient VICON, and the final solution determined using FEA. VICON 'Exact' Strip Method and Wittrick-Williams AlgorithmAs stated previously VICON analyses...

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“…Later, in a different context, Langley [27] took the in-plane motion into consideration, and analyzed the dynamic response of stiffened shell structure. Watson et al [28] used Lagrangian multipliers to model point supports of Levy-type plates based on exact strip method, and thus they performed vibration and buckling analysis of stiffened panels. Yin et al [29] proposed a dynamic stiffness model for eccentrically beam-stiffened plates.…”

Section: Introductionmentioning

confidence: 99%