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Methodology for Predicting the Onset of Widespread Fatigue Damage in Lap-Splice JointsNASA has conducted an Airframe Structural Integrity Program to develop the methodology to predict the onset of widespread fatigue damage to lap-splice joints of fuselage structures. Several stress analysis codes have been developed or enhanced to analyze the lap-splice-joint configuration. Fatigue lives in lap-splice-joint specimens and fatigue-crack growth in a structural fatigue test article agreed well with calculations from small-crack theory and fatigue-crack growth analyses with the FASTRAN code. Residual-strength analyses of laboratory specimens and wide stiffened panels were predicted quite well from the critical crack-tip-opening angle (CTOA) fracture criterion and elastic-plastic finite-element analyses (two- or three-dimensional codes and the STAGS shell code).
Document ID
19990017909
Acquisition Source
Langley Research Center
Document Type
Technical Memorandum (TM)
Authors
Newman, J. C., Jr. (NASA Langley Research Center Hampton, VA United States)
Harris, C. E. (NASA Langley Research Center Hampton, VA United States)
Piascik, R. S. (NASA Langley Research Center Hampton, VA United States)
Dawicke, D. S. (NASA Langley Research Center Hampton, VA United States)
Date Acquired
September 6, 2013
Publication Date
December 1, 1998
Subject Category
Composite Materials
Report/Patent Number
L-17799
NAS 1.15:208975
NASA/TM-1998-208975
Funding Number(s)
PROJECT: RTOP 522-18-11-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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