The buckling in compression of panels with square top-hat section stringers

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dc.contributor.author W. S. Hemp en_US
dc.contributor.author K. H. Griffin en_US
dc.date.accessioned 2014-10-21T15:52:06Z
dc.date.available 2014-10-21T15:52:06Z
dc.date.issued 1949 en_US
dc.identifier.other ARC/R&M-2635 en_US
dc.identifier.uri https://reports.aerade.cranfield.ac.uk/handle/1826.2/3174
dc.description.abstract A simplified panel model is described, together with a number of assumptions about the mode of its buckling. The approach to the calculation of the buckling stress is by splitting the panel into a number of flat plates and treating these by the ordinary plate theory. Use of the boundary conditions between these plates leads to a relation between the buckling stress and the variables of the panel geometry. The results thus obtained are compared with two sets of recent experimental work; and an appendix is included to show the effect of initial panel irregularities on the experimental determination of buckling stresses. en_US
dc.relation.ispartofseries Aeronautical Research Council Reports & Memoranda en_US
dc.title The buckling in compression of panels with square top-hat section stringers en_US


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