Fatigue results for both constant-amplitude and random loading are compared on basis of time to failure, where equivalent time to failure based on natural period of vibration is used for constant-amplitude tests; failure occurs sooner for random than for constant-amplitude loading at lower stress levels; at higher stress levels reverse condition is true; pertinence to aircraft structural components.
Experimental investigation of effects of random loading on fatigue life of notched cantilever-beam specimens of 7075-t6 aluminum alloy
NASA -- Memo
National Aeronautics and Space Administration -- Memorandums ; Memo n 4-12-59L
1959
22 pages
Report
English
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