Accession Number : AD0872158
Title : An Equation for Predicting the Residual Static Strength of Stiffened Panels
Descriptive Note : Technical rept.
Corporate Author : ARMY AVIATION MATERIEL LABS FORT EUSTIS VA
Personal Author(s) : Figge, Sr, I E
PDF Url : AD0872158
Report Date : Apr 1970
Pagination or Media Count : 42
Abstract : An equation has been developed to predict the residual static strength of stiffened panels. All parameters in the equation can be evaluated from tests on simple unstiffened specimens. The stiffened panel is treated as a composite material, with the sheet material representing the matrix and the stiffeners representing the fibers. The residual static strength of the cracked sheet, calculated using notch strength analysis, and the proportional limit of the stiffeners are used in the law-of-mixtures equation to calculate the residual static strength of the stiffened panels. Excellent predictions of the residual static strength of stiffened panels have been obtained and are presented for a wide variety of panel configurations, type fasteners, and crack geometry.
Descriptors : *AIRCRAFT PANELS, *COMPOSITE MATERIALS, CRACKS, EXPERIMENTAL DATA, FAILURE(MECHANICS), FRACTURE(MECHANICS), NOTCH TOUGHNESS, PREDICTIONS, RIVETS, STRUCTURAL PROPERTIES, TOUGHNESS
Subject Categories : Aircraft
Laminates and Composite Materials
Distribution Statement : APPROVED FOR PUBLIC RELEASE