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Residual Strength Analyses of Riveted Lap-Splice JointsThe objective of this paper was to analyze the crack-linkup behavior in riveted-stiffened lap-splice joint panels with small multiple-site damage (MSD) cracks at several adjacent rivet holes. Analyses are based on the STAGS (STructural Analysis of General Shells) code with the critical crack-tip-opening angle (CTOA) fracture criterion. To account for high constraint around a crack front, the "plane strain core" option in STAGS was used. The importance of modeling rivet flexibility with fastener elements that accurately model load transfer across the joint is discussed. Fastener holes are not modeled but rivet connectivity is accounted for by attaching rivets to the sheet on one side of the cracks that simulated both the rivet diameter and MSD cracks. Residual strength analyses made on 2024-T3 alloy (1.6-mm thick) riveted-lap-splice joints with a lead crack and various size MSD cracks were compared with test data from Boeing Airplane Company. Analyses were conducted for both restrained and unrestrained buckling conditions. Comparison of results from these analyses and results from lap-splice-joint test panels, which were partially restrained against buckling indicate that the test results were bounded by the failure loads predicted by the analyses with restrained and unrestrained conditions.
Document ID
20000040430
Acquisition Source
Langley Research Center
Document Type
Technical Memorandum (TM)
Authors
Seshadri, B. R. (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
April 1, 2000
Subject Category
Structural Mechanics
Report/Patent Number
NAS 1.15:209856
L-17948
NASA/TM-2000-209856
Report Number: NAS 1.15:209856
Report Number: L-17948
Report Number: NASA/TM-2000-209856
Funding Number(s)
PROJECT: RTOP 538-02-10-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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