Computing Method Applicability Verification of Effective Width of Skin for Stiffened Panels in Compression

Abstract

It is well known that the fuselage and wing mainly consist of thin-skin stiffened panels and the failure load of stiffened panels is hot topic in aircraft engineering. Johnson-Euler equation is used to evaluate the failure loads, thus the effective width computation of skin needs to be determined. Several kinds of methods to calculate the effective width of skin are analyzed to quest for its origin, and their applicability is verified with test results of thin-skin stiffened panel. The results show that, the calculation errors of the effective width calculation methods are less than 10% for the calculation of riveting Z-typed fuselage stiffened panel failure load, and the methods can be helpful to engineers who design thin-skin stiffened panels in compression.

Keywords

• stiffened panel
• johnson-euler equation
• effective width of skin
• buckling
• failure load