Crack propagation in a full-scale wing structure under random flight-simulation loading
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Abstract
Flight-simulation tests were carried out under different loading conditions. Omitting low-amplitude gust cycles had a small effect on the crack rate. Truncation of infrequently occurring high-amplitude gust cycles to a lower level considerably accelerated crack growth. A 25 percent increase of the design stress level induces about 2.5 times faster crack growth. The application of fail-safe loads (100 percent limit load) drastically delayed subsequent crack growth.