NASA NTRS · 19820012301
Fatigue analysis of composite materials using the fail-safe concept
Abstract
If R1 is the probability of having a crack on a flight component and R2 is the probability of seeing this crack propagate between two scheduled inspections, the global failure regulation states that this product must not exceed 0.0000001.
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Stievenard, G.. 1982-01-01. Fatigue analysis of composite materials using the fail-safe concept. https://ntrs.nasa.gov/citations/19820012301
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