Buckling and vibration of any prismatic assembly of shear and compression loaded anisotropic plates with an arbitrary supporting structure

Anderson, M. S.; Williams, F.W.; Wright, Christopher J. H.

doi:10.1016/0020-7403(83)90050-4

Cited by 98 publications

(60 citation statements)

References 3 publications

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“…In practice the series is truncated by choosing a value of q such that acceptable results are obtained by considering only the m for which, in Eqn 1, 0≤m<q if =0 or =1, and -q≤m≤q if 0<<1. Negative values of m denote the use of complex conjugate stiffness matrices in order to reverse the direction of the response, see Anderson et al, (1983). -4l/7, 4l/9, -4l/15, 4l/17, -4l/23, 4l/25.…”

Section: Necessary Information About Viconoptmentioning

confidence: 99%

“…Convergence on the critical buckling load factors or natural frequencies is from above as q is increased and from below as n, the number of point supports, is increased. Eqn 2 below shows the Hermitian overall stiffness and constraint matrix K used by the VICON option of VICONOPT, see Anderson et al, (1983). Only the populated locations contain all the non-zero elements and the superscript H denotes Hermitian transpose.…”

Section: Necessary Information About Viconoptmentioning

confidence: 99%

“…In the case of stiffened panels no such results were found in the literature, so comparisons were made using the finite element package ABAQUS, see Hibbitt et al, (1997), as in Lillico et al, (2000). VICONOPT is a computer program which incorporates the earlier programs VIPASA, see Wittrick and Williams (1974), and VICON, see Anderson et al, (1983). VICONOPT uses a transcendental stiffness matrix approach based on exact solutions to the governing differential equations and covers any prismatic assembly of isotropic, orthotropic or anisotropic plates, each of which can carry any combination of longitudinally invariant in-plane longitudinal, transverse and shear stresses.…”

Section: Introductionmentioning

confidence: 99%

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

Watson

Kennedy

Williams

et al. 2003

Advances in Structural Engineering

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An efficient method for the buckling and vibration analysis of plates or stiffened panels with clamped ends is presented. The method uses Lagrangian multipliers to couple sinusoidal modes with appropriate half-wavelengths of response, thereby enforcing the end conditions at discrete point supports. Clamped ends can usually be modelled accurately using only a few point supports, while arguments from symmetry often enable some of the required end conditions to be satisfied without explicitly applying constraints. In such cases few half-wavelengths are needed to obtain excellent accuracy. Solutions obtained for the simple limiting case of single plates are exact or within 1% of the classical or other reported solutions. Solutions obtained for stiffened panels are in close agreement with those obtained using finite element analysis.

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Section: Necessary Information About Viconoptmentioning

confidence: 99%

Section: Necessary Information About Viconoptmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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

Watson

Kennedy

Williams

et al. 2003

Advances in Structural Engineering

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“…The resulting transcendental eigenproblem requires an iterative solution, which is performed using the WittrickWilliams algorithm 11 . The simplest form of the buckling analysis 12,13 is performed over a range of values of , that usually extends from a value less than the smallest plate width to the length, l, of the panel. The lowest buckling load found for any  is taken to be the critical buckling load for the panel.…”

Section: Strut Theorymentioning

confidence: 99%

Post-buckling of single and multi-bay panels using strut, strip and FE methods

Lillico¹,

Butler²,

Hunt³

et al. 2001

19th AIAA Applied Aerodynamics Conference

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A compressively-loaded stiffened panel has been designed with post-buckling reserve of strength in its skins using the strip program VICONOPT. Comparisons are made with Finite Element single and double bay models. The panel has been shown by VICONOPT to have a stiffener buckling failure mode when an overall sinusoidal imperfection causing increased stiffener compression is present. Such a failure is not seen in a typical single-bay Finite Element model of such panels. However, the failure is confirmed by a double-bay Finite Element model, which is a closer representation of an aerospace application, such as a wing box. A new strut model, following a Shanley type approach has been developed to emphasise the difference between the single and multi-bay responses. The strut model shows good agreement with single bay Finite Element results. It also indicates the presence of an imperfection in the double bay Finite Element model, which may be represented by offsetting the load towards the skin in the strut model. The VICONOPT code is able to design an aerospace panel of realistic dimensions and loading but only when considering linear elastic material properties.

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“…The resulting transcendental eigenproblem requires an iterative solution which is performed using the WittrickWilliams algorithm. 9 The simplest form of the buckling analysis 10,11 is performed over a range of values of  that usually extends from a value less than the smallest plate width to the length, l, of the panel. The lowest buckling load found for any  is taken as the critical buckling load for the panel.…”

Section: Introductionmentioning

confidence: 99%

Optimum design and testing of a post-buckled stiffened panel

Lillico¹,

Butler²,

Hunt³

et al. 2000

41st Structures, Structural Dynamics, and Materials Conference and Exhibit

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The efficient, industrially used, linear elastic preliminary design software VICONOPT is employed to design a stiffened panel with a post-buckled reserve of strength. The initial buckling mode is a local skin mode in longitudinal compression with allowance being made for the effects of an initial overall imperfection. The resulting panel has been analyzed using the non-linear FE package ABAQUS and four laboratory specimens have been tested to failure. The similarity of the experimental failure with the VICONOPT and ABAQUS predictions suggests that VICONOPT can give a satisfactory preliminary design. While neither model matches completely the boundary conditions found in a real aircraft compression panel, it is suggested that the VICONOPT model may be a better representation than either the ABAQUS model or the experimental tests.

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Buckling and vibration of any prismatic assembly of shear and compression loaded anisotropic plates with an arbitrary supporting structure

Cited by 98 publications

References 3 publications

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

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

Post-buckling of single and multi-bay panels using strut, strip and FE methods

Optimum design and testing of a post-buckled stiffened panel

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