Fatigue Crack Growth in Weldbonded Aluminum Alloy Stiffened Panels under Pressure Loading.
Research and development rept.,
DAVID W TAYLOR NAVAL SHIP RESEARCH AND DEVELOPMENT CENTER BETHESDA MD
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An experimental study was conducted to characterize the fatigue crack growth behavior of stiffened panels under uniform lateral pressure loading. The panels were made of standard 5456 aluminum alloy and fabricated by weldbonding. Fatigue failure of the panels consisted of cracking of the stiffness followed by cracking of the skin. Crack growth rate data showed a maximum value in the stiffeners and a constant value in the skin before failure. A weldbonded stiffened panel could endure more fatigue cycles than a gas metal arc welded panel under similar loading. The panel data were correlated with base line materials data and represented by either of two simple equations in terms of fatigue crack growth rate versus stress intensity factor range. The stress intensity analysis for the panels was made by an approximation method considering the combined effects of tension and bending stresses. Accuracy of this method was verified by photoelastic measurements. Author
- Metallurgy and Metallography
- Fabrication Metallurgy