dc.contributor.author |
Hemp, W. S. |
|
dc.contributor.author |
Griffin, K. H. |
|
dc.date.accessioned |
2012-05-15T14:48:26Z |
|
dc.date.available |
2012-05-15T14:48:26Z |
|
dc.date.issued |
1949-06 |
|
dc.identifier.uri |
http://dspace.lib.cranfield.ac.uk/handle/1826/7154 |
|
dc.description.abstract |
A simplified panel model is described, together with a number of assumptions about the mode of its bucking. 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_UK |
dc.language.iso |
en |
en_UK |
dc.publisher |
College of Aeronautics, Cranfield |
en_UK |
dc.relation.ispartofseries |
College Report |
en_UK |
dc.relation.ispartofseries |
29 |
en_UK |
dc.title |
The buckling in compression of panels with square top-hat section stringers |
en_UK |
dc.type |
Report |
en_UK |