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Fatigue analysis of composite materials using the fail-safe conceptIf 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.
Document ID
19820012301
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Stievenard, G. (NASA Headquarters Washington, DC United States)
Date Acquired
September 4, 2013
Publication Date
January 1, 1982
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
NASA-TM-76671
NAS 1.15:76671
Report Number: NASA-TM-76671
Report Number: NAS 1.15:76671
Accession Number
82N20175
Funding Number(s)
CONTRACT_GRANT: NASW-3542
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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