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Analysis of cold worked holes for structural life extension

Author
Wieland, David H.
Published
Sep 1, 1994.
Physical Description
1 electronic document
Additional Creators
Cardinal, Joseph W., Burnside, O. Hal, and Cutshall, Jon T.
Online Version

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Unclassified, Unlimited, Publicly available.
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Summary
Cold working holes for improved fatigue life of fastener holes are widely used on aircraft. This paper presents methods used by the authors to determine the percent of cold working to be applied and to analyze fatigue crack growth of cold worked fastener holes. An elastic, perfectly-plastic analysis of a thick-walled tube is used to determine the stress field during the cold working process and the residual stress field after the process is completed. The results of the elastic/plastic analysis are used to determine the amount of cold working to apply to a hole. The residual stress field is then used to perform damage tolerance analysis of a crack growing out of a cold worked fastener hole. This analysis method is easily implemented in existing crack growth computer codes so that the cold worked holes can be used to extend the structural life of aircraft. Analytical results are compared to test data where appropriate.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19950013077.
Accession ID: 95N19493.
NASA. Langley Research Center, FAA(NASA International Symposium on Advanced Structural Integrity Methods for Airframe Durability and Damage Tolerance, Part 2; p 947-961.
Terms of Use and Reproduction
No Copyright.
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