SYMPOSIA PAPER Published: 01 January 1967

Crack Propagation and Residual Static Strength of Fatigue-Cracked Titanium and Steel Cylinders


Flight safety of the U. S. supersonic transport (SST) requires design data on the rate of crack propagation and the residual static strength of fatigue cracked cylinders. To provide these data an experimental test program was conducted on stiffened cylinders and curved and flat panels of titanium sheet (8A1-1Mo-1V duplex annealed) in the environments representative of SST operations (−110 F, room temperature, and +550 F) and on similar specimens of a candidate steel sheet material (PH-14-8Mo SRH 1050) at room temperatures. Cyclic pressure loading was applied to the cylinders and curved panels. Variation of hoop cross-section area and spacing on longitudinally stiffened cylinders provided design criteria for the crack-arresting properties of hoops in typical fuselage applications. Tension tests of flat panels with and without longitudinal straps provided data on material residual strengths and on the strap attachment qualities in the presence of transverse fatigue cracks. The experimental data were analyzed by means of several analytical formulas so that the design data could be interpreted and presented in compact and usable form.

Author Information

Crichlow, W., J.
Lockheed-California Co., Burbank, Calif.
Wells, R., H.
Lockheed-California Co., Burbank, Calif.
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Developed by Committee: E08
Pages: 25–70
DOI: 10.1520/STP47227S
ISBN-EB: 978-0-8031-6910-4
ISBN-13: 978-0-8031-6633-2