Stiffened aircraft panels are often designed to operate in the postbuckled mode, therefore suitable prediction methods for stiffener crippling and short-column buckling need to be developed for new aircraft materials such as Fiber Metal Laminates. For crippling, a total of three methods are evaluated. One completely new method proposed here, the second based on flat plate element testing, while the third is an already existing method for metallic materials, Needham's method.
Crippling and Short-Column Buckling of Fiber Metal Laminates
1994
38 pages
Report
No indication
English
On buckling of stringer panels including forced crippling
Engineering Index Backfile | 1955
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