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Comparison of the structural efficiency of panels having straight-web and curved-web Y-section stiffeners

Description: Report presenting comparisons of the structural efficiency of panels with straight-web and curved-web Y-section stiffeners. In the high-stress region in which failure is at least in part associated with local buckling, panels with curved-web Y-section stiffeners have higher structural efficiencies than panels with straight-web Y-section stiffeners, which is evidenced by higher average stresses at failure, smaller stiffener heights, or wider average spacing of rivet lines.
Date: January 1949
Creator: Dow, Norris F. & Hickman, William A.
Partner: UNT Libraries Government Documents Department

Design charts for flat compression panels having longitudinal extruded Y-section stiffeners and comparison with panels having formed Z-section stiffeners

Description: Report presenting design charts for 24S-T and 75S-T aluminum-alloy flat compression panels with longitudinal extruded Y-section stiffeners. Comparisons are also made among panels designed from these charts and 24S-T aluminum-alloy panels with formed Z-section stiffeners designed from available design charts.
Date: August 1947
Creator: Dow, Norris F. & Hickman, William A.
Partner: UNT Libraries Government Documents Department

Direct-reading design charts for 75S-T aluminum-alloy flat compression panels having longitudinal straight-web Y-section stiffeners

Description: "Direct-reading design charts are presented for 75S-T aluminum-alloy flat compression panels having longitudinal straight-web Y-section stiffeners. These charts make possible the direct determination of the stress and all panel proportions required to carry a given intensity of loading with a given skin thickness and effective length of panel" (p. 1).
Date: August 1948
Creator: Dow, Norris F. & Hickman, William A.
Partner: UNT Libraries Government Documents Department

Effect of variation in diameter and pitch of rivets on compressive strength of panels with Z-section stiffeners: 1: panels with close stiffener spacing that fail by local buckling

Description: From Summary: "An experimental investigation is being conducted to determine the effect of varying the rivet diameter and pitch on the compressive strength of 24S-T aluminum-alloy panels with longitudinal Z-section stiffeners." The average stress at failing load for each rivet diameter, depth of countersink, and pitch of rivet is provided.
Date: August 1945
Creator: Dow, Norris F. & Hickman, William A.
Partner: UNT Libraries Government Documents Department

Effect of variation in diameter and pitch of rivets on compressive strength of panels with Z-section stiffeners: Panels of various lengths with close stiffener spacing

Description: Report presenting an experimental investigation conducted to determine the effect of varying rivet diameter and pitch on the compressive strength of flat 24S-T aluminum-alloy panels with longitudinal Z-section stiffeners of the type for which design charts are available.
Date: September 1947
Creator: Dow, Norris F. & Hickman, William A.
Partner: UNT Libraries Government Documents Department

Effect of variation in diameter and pitch of rivets on compressive strength of panels with Z-section stiffeners panels of various stiffener spacings that fail by local buckling

Description: Report presenting an investigation conducted to determine the effect of varying the rivet diameter and pitch on the compressive strength of flat 24S-T aluminum-alloy Z-stiffened panels of the type for which design charts are available. The primary focus of the investigation is concerned with panels which have the smallest values of width-to-thickness ratio of the webs of the stiffeners given by the design charts and have such length that failure is by local buckling.
Date: October 1947
Creator: Dow, Norris F. & Hickman, William A.
Partner: UNT Libraries Government Documents Department

Effect of variation in diameter and pitch of rivets on compressive strength of panels with Z-section stiffeners: Panels that fail by local buckling and have various values of width-to-thickness ratio for the webs of the stiffeners

Description: Report presenting an experimental investigation to determine the effect of varying the rivet diameter and pitch on the compressive strength of flat 24S-T aluminum-alloy Z-stiffened panels of the type for which design charts are available. The current investigation is concerned with panels which have various values of width-to-thickness ratio of the webs of the stiffeners and have such length that failure is by local buckling.
Date: November 1948
Creator: Dow, Norris F. & Hickman, William A.
Partner: UNT Libraries Government Documents Department

Effect of Variation in Rivet Diameter and Pitch on the Average Stress at Maximum Load for 24S-T3 and 75S-T6 Aluminum-Alloy, Flat, Z-Stiffened Panels That Fail by Local Instability

Description: "A study is made of the effect of variation in diameter and pitch of A17S-T4 aluminum-alloy flat-head rivets on the average stress at maximum load for 24S-T3 and 75S-T6 aluminum-alloy, flat, Z-stiffened panels that fail by local instability. A curve is presented for determining the diameter and pitch required to insure the development of a given average stress for local instability" (p. 1).
Date: July 1950
Creator: Dow, Norris F. & Hickman, William A.
Partner: UNT Libraries Government Documents Department

Preliminary Experiments on the Elastic Compressive Buckling of Plates With Integral Waffle-Like Stiffening

Description: Memorandum presenting an experimental investigation of the elastic compressive buckling strength of plates with various configurations of integral stiffening. Some of the configurations tested included ribbing that was longitudinal, transverse, longitudinal, and transverse, and skewed at various angles to the sides of the plates to form a diamond or waffle-like pattern. The results indicate that the waffle-like stiffening is of sufficient structural interest to merit further study of the plastic buckling and fabrications aspects.
Date: July 28, 1952
Creator: Dow, Norris F. & Hickman, William A.
Partner: UNT Libraries Government Documents Department

Preliminary investigation of the relation of the compressive strength of sheet-stiffener panels to the diameter of rivet used for attaching stiffeners to sheet

Description: Report discusses the results of compressive testing of 24S-T aluminum-alloy sheet-stiffener panels with five ratios of stiffener thickness to sheet thickness. For each ratio, rivets of five different diameters were used to attach the stiffeners to the sheets. The compressive strengths were found to increase with an increase in the diameter of the rivets until the ratio of rivet diameter to over-all thickness reached a certain point.
Date: November 1944
Creator: Dow, Norris F. & Hickman, William A.
Partner: UNT Libraries Government Documents Department

Structural Evaluation of an Extruded Magnesium-Alloy T-Stiffened Panel

Description: Note presenting compressive tests made of six different lengths of a ZK60A magnesium-alloy flat panel with skin and longitudinal T-section stiffeners extruded as one integral unit. The results indicated that the extruded panel had structural characteristics somewhere between those for 24S-T and 75S-T aluminum-alloy construction, but required far fewer rivets to assemble than those panels.
Date: February 1948
Creator: Dow, Norris F. & Hickman, William A.
Partner: UNT Libraries Government Documents Department

Compressive-strength comparisons of panels having aluminum-alloy sheet and stiffeners with panels having magnesium-alloy sheet and aluminum alloy stiffeners

Description: Report presenting comparisons of 24S-T aluminum-alloy flat compression panels with longitudinal Z-section stiffeners and panels with flat FS-1E magnesium-alloy sheet and longitudinal 24S-T aluminum-alloy Z-section stiffeners. The use of the composite magnesium-alloy, aluminum-alloy construction permits wider stiffener spacing with little to not loss in structural efficiency or stress for local buckling. Results regarding stiffener spacing, proportions, and consideration of the different material constructions are provided.
Date: April 1947
Creator: Dow, Norris F.; Hickman, William A. & McCracken, Howard L.
Partner: UNT Libraries Government Documents Department

Data on the compressive strength of skin-stringer panels of various materials

Description: "Flat skin-stringer compression panels of stainless steel, mild steel, titanium, copper, four aluminum alloys, and a magnesium alloy were tested. The results show the effect of variations in yield stress, Young's modulus, and both yield stress and Young's modulus for constant yield strain on the average stress at maximum load, on the stress for local buckling, and on the load-shortening characteristics of the panels" (p. 1).
Date: January 1954
Creator: Dow, Norris F.; Hickman, William A. & Rosen, B. Walter
Partner: UNT Libraries Government Documents Department

Effect of Variation in Rivet Strength on the Average Stress at Maximum Load for Aluminum-Alloy, Flat, Z-Stiffened Compression Panels That Fail by Local Buckling

Description: "A study is made of the effect of variation in rivet strength on the average panel stress at maximum load for 75S-T6 aluminum-alloy, flat, Z-stiffened compression panels that fail by local buckling. A curve is presented for the determination of the relationship between strength, diameter, and pitch of the rivets, and the strength of stiffened, flat compression panels of such proportions that failure is by local buckling" (p. 1).
Date: June 1953
Creator: Dow, Norris F.; Hickman, William A. & Rosen, B. Walter
Partner: UNT Libraries Government Documents Department

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

Description: Report presenting results for a part of a test program on 24S-T aluminum-alloy flat compression panels with longitudinal formed hat-section stiffeners. This particular part of the program is concerned with panels in which the thickness of the stiffener material is equal to the thickness of the skin. Results regarding the hat-stiffened panels and a comparison of hat-stiffened and Z-stiffened panels are provided.
Date: September 1947
Creator: Hickman, William A. & Dow, Norris F.
Partner: UNT Libraries Government Documents Department

Compressive strength of 24S-T aluminum-alloy flat panels with longitudinal formed hat-section stiffeners having four ratios of stiffener thickness to skin thickness

Description: Report presenting results for a test program on 24S-T aluminum-alloy flat compression panels with longitudinal hat-section stiffeners. The results for panels in which the thicknesses of the stiffener material are 0.39 and 1.25 times the skin thickness are presented and incorporated with previously provided results. These results are presented in tabular and graphical form and show the effect of the relative dimensions of a panel on the buckling stress and the average stress at failure.
Date: March 1948
Creator: Hickman, William A. & Dow, Norris F.
Partner: UNT Libraries Government Documents Department

Data on the Compressive Strength of 75S-T6 Aluminum-Alloy Flat Panels Having Small, Thin, Widely Spaced, Longitudinal Extruded Z-Section Stiffeners

Description: "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" (p. 1).
Date: November 1949
Creator: Hickman, William A. & Dow, Norris F.
Partner: UNT Libraries Government Documents Department

Data on the Compressive Strength of 75S-T6 Aluminum-Alloy Flat Panels with Longitudinal Extruded Z-Section Stiffeners

Description: "The experimental results are presented for a 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 concerned with panels in which the ratio of the thickness of the stiffener material to the skin material varies from 0.4 to 1.0 and the ratio of stiffener spacing to skin thickness varies from 15 to 40" (p. 1).
Date: March 1949
Creator: Hickman, William A. & Dow, Norris F.
Partner: UNT Libraries Government Documents Department

Direct-reading design charts for 24S-T3 aluminum-alloy flat compression panels having longitudinal formed hat-section stiffeners and comparisons with panels having Z-section stiffeners

Description: Report presenting direct-reading design charts for 24S-T3 aluminum-alloy flat compression panels with longitudinal formed hat-section stiffeners. The charts make it possible to directly determine the stress and all panel proportions required to carry a given intensity of loading with a given skin thickness and effective length of panel. Results regarding simple compression, combined compression and bending, and combined compression, bending, and shear are provided.
Date: March 1953
Creator: Hickman, William A. & Dow, Norris F.
Partner: UNT Libraries Government Documents Department

Direct-reading design charts for 75S-T6 aluminum-alloy flat compression panels having longitudinal extruded Z-section stiffeners

Description: "Direct-reading design charts are presented for 75S-T6 aluminum-alloy flat compression panels having longitudinal extruded Z-section stiffeners. These charts, which cover a wide range of proportions, make possible the direct determination of the stress and all panel dimensions required to carry a given intensity of loading with a given skin thickness and effective length of panel" (p. 1).
Date: February 1952
Creator: Hickman, William A. & Dow, Norris F.
Partner: UNT Libraries Government Documents Department