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FlexureTorsion Failure of Panels

FlexureTorsion Failure of Panels FAILURE of panels under static compression, or for that matter under any loads, involves a vast array of problems ranging from properties of material to initial instability and postbuckling phenomena as occurring in various types of panels. It is not intended here to do justice to all these aspects of the subject but to select a singlebut at the same time very importanttopic, develop its analysis as fully as possible, and present the results in a readily applicable form. The structure investigated is the single skin stiffened panel under compression and the mode of failure considered, denoted by flexural cum torsional failure, involves predominantly flexure and torsion of the stringer with a wavelength of greater order of magnitude than stringer height and pitch. By torsional deformation of the stringer we understand a rotation of its undistorted crosssection about a longitudinal axis R in the plane of the plate, the position of which will be selected later on see FIG. 1b. The panel may, of course, also fail in a local mode of stringer and plate with a short wavelength of the order of magnitude of stringer height and pitch, but the analysis of this case is not included here see, however, Argyris and Dunne. Note that a local mode of deformation of a stringer formed by straight walls is commonly defined as a distortion of the crosssection in which the longitudinal edges where two adjacent walls meet remain straight see FIG. 1c. http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png Aircraft Engineering and Aerospace Technology Emerald Publishing

FlexureTorsion Failure of Panels

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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb032433
Publisher site
See Article on Publisher Site

Abstract

FAILURE of panels under static compression, or for that matter under any loads, involves a vast array of problems ranging from properties of material to initial instability and postbuckling phenomena as occurring in various types of panels. It is not intended here to do justice to all these aspects of the subject but to select a singlebut at the same time very importanttopic, develop its analysis as fully as possible, and present the results in a readily applicable form. The structure investigated is the single skin stiffened panel under compression and the mode of failure considered, denoted by flexural cum torsional failure, involves predominantly flexure and torsion of the stringer with a wavelength of greater order of magnitude than stringer height and pitch. By torsional deformation of the stringer we understand a rotation of its undistorted crosssection about a longitudinal axis R in the plane of the plate, the position of which will be selected later on see FIG. 1b. The panel may, of course, also fail in a local mode of stringer and plate with a short wavelength of the order of magnitude of stringer height and pitch, but the analysis of this case is not included here see, however, Argyris and Dunne. Note that a local mode of deformation of a stringer formed by straight walls is commonly defined as a distortion of the crosssection in which the longitudinal edges where two adjacent walls meet remain straight see FIG. 1c.

Journal

Aircraft Engineering and Aerospace TechnologyEmerald Publishing

Published: Jun 1, 1954

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