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A Practical Engineering Approach to Predicting Fatigue Crack Growth in Riveted Lap JointsAn extensive experimental database has been assembled from very detailed teardown examinations of fatigue cracks found in rivet holes of fuselage structural components. Based on this experimental database, a comprehensive analysis methodology was developed to predict the onset of widespread fatigue damage in lap joints of fuselage structure. Several computer codes were developed with specialized capabilities to conduct the various analyses that make up the comprehensive methodology. Over the past several years, the authors have interrogated various aspects of the analysis methods to determine the degree of computational rigor required to produce numerical predictions with acceptable engineering accuracy. This study led to the formulation of a practical engineering approach to predicting fatigue crack growth in riveted lap joints. This paper describes the practical engineering approach and compares predictions with the results from several experimental studies.
Document ID
20000038233
Acquisition Source
Langley Research Center
Document Type
Technical Memorandum (TM)
Authors
Harris, C. E. (NASA Langley Research Center Hampton, VA United States)
Piascik, R. S. (NASA Langley Research Center Hampton, VA United States)
Newman, J. C., Jr. (NASA Langley Research Center Hampton, VA United States)
Date Acquired
September 7, 2013
Publication Date
May 1, 2000
Subject Category
Metals And Metallic Materials
Report/Patent Number
NASA/TM-2000-210106
L-17956
NAS 1.15:210106
Funding Number(s)
PROJECT: RTOP 706-11-11-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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