| dc.creator |
Hemp, W. S. |
|
| dc.creator |
Griffin, K. H. |
|
| dc.date |
2012-05-15T14:48:26Z |
|
| dc.date |
2012-05-15T14:48:26Z |
|
| dc.date |
1949-06 |
|
| dc.date.accessioned |
2022-05-09T10:17:17Z |
|
| dc.date.available |
2022-05-09T10:17:17Z |
|
| dc.identifier |
http://dspace.lib.cranfield.ac.uk/handle/1826/7154 |
|
| dc.identifier.uri |
https://reports.aerade.cranfield.ac.uk/handle/1826.2/4706 |
|
| dc.description |
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. |
|
| dc.language |
en |
|
| dc.publisher |
College of Aeronautics, Cranfield |
|
| dc.relation |
College Report |
|
| dc.relation |
29 |
|
| dc.title |
The buckling in compression of panels with square top-hat section stringers |
|
| dc.type |
Report |
|