Compressive Strength Of 24s T Aluminum Alloy Flat Panels With Longitudinal Formed Hat Section Stiffeners Having A Ratio Of Stiffener Thickness To Skin Thickness Equal To 1 00

Results are present for part of a test program on 24S-T aluminum-alloy flat compression panels with hat-section stiffeners. The results show the effect of the relative dimensions of a panel on the buckling stress and average stress at maximum load. Comparative envelope curves are presented to provide some indication of the relative structural efficiencies of hat- and Z-stiffened panels having a ratio of stiffener thicknews to skin thickness of one.

Results are presented for a test program on 24S-T aluminum-alloy flat compression panels with longitudinal formed hat-section stiffeners. This paper presents the results for panels in which the thicknesses of the stiffener material are 0.39, 0.63, 1.00, and 1.25 times the skin thickness. The results show the effect of the relative dimensions of a panel on the buckling stress and the average stress of failure.

The experimental results are presented for the second part of an investigation of the compressive strength of 75S-T6 aluminum-alloy flat panels with longitudinal extruded Z-section stiffeners. This part of the investigation is particularly concerned with panels in which the ratio of the thickness of the stiffener material to the skin material is small and the ratio of stiffener spacing to skin thickness is large.