Stress in a Curved Skin Panel of a Pressurized Fuselage: An Analysis of a Particular Stressing Case

Abstract

The problem solved is that of an initially curved circumferential skin strip, representing a section of the panel midway between frames, continuous over the stringers which act as sinking supports and transfer part of the internal pressure load to the frames. The remainder of the pressure load produces hoop tension in the skin strip, but the maximum total stress including bending in the skin at the stringer, which is evaluated, is usually greater than would arise from hoop tension alone, in an unstiffened shell.

Citation

Lockwood Taylor, J. (1957), "Stress in a Curved Skin Panel of a Pressurized Fuselage: An Analysis of a Particular Stressing Case", Aircraft Engineering and Aerospace Technology, Vol. 29 No. 7, pp. 216-218. https://doi.org/10.1108/eb032852